Entries |
Document | Title | Date |
20080201025 | Method of Distributing Braking Within at Least One Group of Brakes of an Aircraft - The invention provides a method of managing the braking of an aircraft having a plurality of brakes comprising friction elements, the method comprising the following steps for at least one group ( | 08-21-2008 |
20080201026 | METHOD AND A DEVICE FOR CONTROLLING THE GROUND CLEARANCE OF AN AIRCRAFT - The present invention relates to a method and to a device for controlling and adjusting the ground clearance (h) of an aircraft ( | 08-21-2008 |
20080208396 | Mission Control System and Vehicle Equipped with the Same - There is described a mission control system having an operator seat; a head-mounted display and digital gloves worn by the operator; a headset having a microphone and integrated in the head-mounted display; a tracker for tracking the movements of the head-mounted display and the digital gloves; and a mission computer housed in the operator seat and connected to the head-mounted display, to the digital gloves, to the headset, to the microphone, and to the tracker, to allow the operator to impart gestural commands by means of the digital gloves, and voice commands by means of the microphone, and to receive visual information by means of the head-mounted display, and audio information by means of the headset. | 08-28-2008 |
20080208397 | LOGISTICS SYSTEM TO SUPPORT DEPLOYED ASSETS WITH OVER THE HORIZON CONNECTIVITY - A logistic systems to support deployed platforms that includes a reporting system located within deployed assets, an over-the-horizon (OTH) communication system, an information distribution node, a logistics control system, and a servicing activity. The reporting system located within deployable assets monitors and reports deployed asset status information using the OTH communication system. Thus, the reporting system passes deployed asset status information to the logistics controller via the information distribution node. The logistics controller receives deployed asset status information and allocates the necessary resources to service the deployed asset based on received deployed asset status information. This allocation of resources is coordinated at the servicing activity or service depot in communication with the logistics controller prior to the arrival of the deployed asset saving valuable time. | 08-28-2008 |
20080208398 | Energy Protecting Device for Aircraft - The invention concerns a device ( | 08-28-2008 |
20080215192 | INTERACTIVE DEVICE FOR LEGACY COCKPIT ENVIRONMENTS - Disclosed is an aircraft computing and display device that includes a general purpose processor, a touch screen display and a housing. The processor executes logical instructions in the form of computer software. The touch screen display forms an interactive human-machine interface by displaying video graphics and accepting user input with a pressure sensitive surface. The housing retains the processor and the touch screen and is physically configured to replace a legacy device mounted in a cockpit instrument panel of the aircraft. | 09-04-2008 |
20080215193 | ELECTRONIC FLIGHT BAG HAVING FILTER SYSTEM AND METHOD - A system and method for filtering information from an electronic flight bag system (EFB) used on a mobile platform, for example, on an aircraft. In one embodiment the system makes use of an EFB having a display with a selection to enable a filter. When the filter is enabled, the user is presented with a plurality of options for limiting retrieved information to only specific types of information or data. This allows one, two or more layers of filtering to be implemented on the information that is searched and obtained from the EFB, and enables a limited subset of information to be obtained that is available for viewing on a display associated with the EFB. The system and method eliminates or significantly reduces the amount of non-relevant information that the crew members are required to review when attempting to obtain specific types of information from the EFB. | 09-04-2008 |
20080215194 | FORMULATION OF A PREVENTIVE MAINTENANCE MESSAGE RELATING TO THE FUNCTIONAL DEGRADATIONS OF AN AIRCRAFT - A method of preventive maintenance is disclosed for an aircraft. The aircraft includes components, including items of equipment of the aircraft and/or electronic modules and/or physical links. The lifetime information for the components is known. The aircraft also includes means for monitoring the components, a centralized maintenance system, and means for estimating the life time of the components. The aircraft carries out a set of functions, each being ensured by a chain of components. The method comprises several steps including, a first step of locating the degradations of the items of equipment, a second step making it possible to allocate the located degradations to the various functions of the aircraft, a third step of estimating the lifetime of the functions identified in the second step, and a fourth step of formulating the maintenance message constructed on the basis of the previous steps. | 09-04-2008 |
20080221745 | COLLECTION AND DISTRIBUTION SYSTEM - A collection and distribution system wherein information is collected from one or more aerial vehicles and from one or more ground-based sources before being processed and provided to an end-user. | 09-11-2008 |
20080228330 | On-Demand Flight Data Service - A flight data service subscription system allows personnel to subscribe to flight data services using an electronic devices such as a multifunctional display (MFD) onboard an aircraft. The MFD is used to select regional areas of coverage and generate requests for subscriptions to flight data services. Flight data application software running on the MFD manages flight data and the subscription requests. A server operated by a flight data service provider receives the subscription requests from the MFD and dispatches flight data responsive to the requests for the selected region. A wireless local area network on the ground transfers flight data and subscription requests between the MFD and the flight data subscription server. | 09-18-2008 |
20080228331 | SYSTEM AND METHOD FOR MEASURING PARAMETERS AT AIRCRAFT LOCI - A system for measuring parameters at a plurality of loci associated with an aircraft includes: (a) a central unit; (b) a plurality of communicating nodes coupled with the central unit; and (c) a respective plurality of sensing units associated with each respective communicating node of the plurality of communicating nodes; at least one selected sensing unit of at least one respective plurality of sensing units being a remote sensing unit. The at least one remote sensing unit communicates wirelessly with the respective communicating node. | 09-18-2008 |
20080234879 | GROUND FAULT INTERRUPTION USING DSP BASED SSPC MODULE - A ground fault interruption (GFI) system is incorporated onto a DSP based LRM of an aerospace vehicle. The GFI system operates with digital controls and, unlike the prior art, the system does not employ current transformers. Synchronization pulses are employed to coordinate instantaneous current measurement samplings in each phase of a multi-phase power system. Coordinated sampling may reduce phase angle current differential errors and improve operational precision of the GFI system. | 09-25-2008 |
20080243313 | GOVERNOR FOR A ROTOR WITH A VARIABLE MAXIMUM COLLECTIVE PITCH - A governor configured to regulate the rotational velocity of one or more rotors of an aircraft by adjusting a collective blade pitch of the one or more rotors. In one embodiment, the governor comprises a control monitor, a maximum pitch module, a rotor module, and a pitch adjustment module. The control monitor is configured to monitor one or more flight control inputs that are controllable by an operator of the aircraft. The maximum pitch module is configured to dynamically determine a maximum collective blade pitch based on the one or more flight control inputs monitored by the control monitor. The rotor module is configured to monitor information related to the rotational velocity of the one or more rotors. The pitch adjustment module is configured to (i) receive information related to the rotational velocity of the one or more rotors from the rotor module and (ii) adjust the collective blade pitch of the one or more rotors to regulate the rotational velocity of the one or more rotors. | 10-02-2008 |
20080249669 | Device at an airborne vehicle and a method for collision avoidance - A device at an airborne vehicle including a flight control system configured to control the behaviour of the airborne vehicle based on acceleration commands, a first control unit configured to provide the acceleration commands to the flight control system, and a collision avoidance unit. The collision avoidance unit includes a detection unit arranged to detect whether the airborne vehicle is on a collision course and a second control unit arranged to feed forced acceleration commands to the flight control system upon detection that the airborne vehicle is on a collision course. A method for collision avoidance in an airborne vehicle. | 10-09-2008 |
20080249670 | Method and Device for Carrying Out at Least One Flight Testing on an Aircraft and the Use Thereof - The inventive device ( | 10-09-2008 |
20080249671 | Method and Device For Providing an Multi-Engine Aircraft Pilot With Data Concerning Said Engines - The invention concerns a device ( | 10-09-2008 |
20080255713 | Dynamic Adjustment of Wing Surfaces for Variable Camber - The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity, vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces. | 10-16-2008 |
20080262663 | METHOD FOR MONITORING PLANE ENGINES - A method for monitoring plane engines The present invention relates to a method for monitoring engines of a plane comprising at least two engines (m | 10-23-2008 |
20080269962 | Method and a system for determining and indicating a sound nuisance level outside an aircraft - A method of determining a sound nuisance level outside an aircraft, in which method:
| 10-30-2008 |
20080275597 | BALANCING THE POWER OF TWO TURBOSHAFT ENGINES OF AN AIRCRAFT - The present invention relates to a method and to an associated fuel metering system for balancing the power delivered by two aircraft turboshaft engines by determining first and second limiting margins of the engines (M | 11-06-2008 |
20080288130 | SYSTEM FOR SELECTING DATA REPRESENTING AN AIR PARAMETER, PROCESS AND COMPUTER PROGRAM RELATING TO THE SAME - A system for selecting a datum among a set of data representing an air parameter, this set comprising at least two engine data obtained by measurement respectively in the zone of two engines of an aircraft and at least two reference data obtained by measurement in the zone of the fuselage of the aircraft, the system comprising:
| 11-20-2008 |
20080294303 | Onboard execution of flight recorder application - An apparatus in an example comprises an onboard controller and a flight recorder application. The onboard controller is onboard a vehicle and comprises an onboard operating system (OS). The flight recorder application is executable onboard the vehicle by the onboard operating system. | 11-27-2008 |
20080294304 | Method for Optimizing a Fuel Consumption of an Aircraft During the Flight Thereof - The invention relates to a method for optimizing the fuel consumption of an aircraft during flight. At a given point of the flight, a fuel excess (EXTRA) is determined relative to the statutory loads depending on the flight profile and weather conditions forecast for the rest of the flight. If the excess (EXTRA) is less than a given value (EXTRA-mini), for at least one of the forthcoming flight phases ( | 11-27-2008 |
20080294305 | ROTORCRAFT CONTROL SYSTEM | 11-27-2008 |
20080294306 | METHOD AND DEVICE FOR MONITORING A POSITION INDICATION OF AN AIRCRAFT - The device ( | 11-27-2008 |
20080300735 | TERRAIN AUGMENTED DISPLAY SYMBOLOGY - Terrain augmented display symbology improves a pilot's spatial awareness during aircraft approach and landing. The symbology includes a terrain-tracing, three-dimensional centerline that provides a visual cue of terrain elevations along an approach course to a runway. Additionally, the symbology includes terrain-tracing, three-dimensional lateral deviation marks representing deviations from the centerline. The symbology also includes an aircraft symbol shaped like an airplane and pointing towards the direction of travel. The pilot may be able to quickly interpret the terrain augmented display symbology and take actions based on the surrounding terrain elevation. | 12-04-2008 |
20080300736 | SYSTEM AND METHOD FOR CONTROLLING THE SPEED OF AN AIRCRAFT - A system and method are disclosed for controlling the speed of an aircraft having a preprogrammed speed profile when transitioning from a manually set target speed to the preprogrammed speed profile. In operation, an input is received indicating that a user desires to transition from a manually set target speed to the preprogrammed speed profile. A determination is then made as to whether the manually set target speed satisfies one or more selected conditions for qualifying as a constraint speed of the preprogrammed speed profile. If the manually set target speed satisfies the one or more selected conditions, the preprogrammed speed profile is updated to include the manually set target speed as a constraint speed and the speed of the aircraft is controlled using the updated speed profile. | 12-04-2008 |
20080300737 | METHOD AND DEVICE FOR CALCULATING A FLIGHT PLAN - The invention relates to a method for calculating a diversion flight plan making it possible to define at least one diversion airport to have the associated predictions on the corresponding diversion flight plan. The invention also relates to a device comprising means implementing the method according to the invention. The device according to the invention makes it possible to change, in the course of the flight, the said waypoint from which the diversion flight plan is calculated. The method according to the invention furthermore calculates the last possible diversion point on the flight plan, based on the fuel predictions. | 12-04-2008 |
20080300738 | METHOD OF OPTIMIZING A FLIGHT PLAN - A method of optimizing a flight plan of an aircraft used in a flight management system of an aircraft is disclosed. This method makes it possible to constrain the real cost index of the mission executed to the optimal cost index CI | 12-04-2008 |
20080306637 | BATTERY NETWORK SYSTEM WITH LIFE-OPTIMAL POWER MANAGEMENT AND OPERATING METHODS THEREOF - A system and methods for life optimal power management of a distributed or centralized battery network system for use in aircraft functions and subsystems are disclosed. The method determines power priority of the subsystems, and selectively distributes power from the battery network system to the subsystems based on the power priority. Concurrently with distributing power, the method manages the energy in the battery network system. To determine whether the battery power is sufficient for aircraft functions, the method also computes and indicates the actual available energy left in the battery network systems. With this approach, the system and methods can provide a persistent power supply in the event an unexpected battery failure occurs, thereby enabling the aircraft to safely maintain flight operability despite a battery failure. | 12-11-2008 |
20080306638 | METHOD AND DEVICE TO ASSIST IN NAVIGATION IN AN AIRPORT SECTOR - The invention relates to a method and device to assist in navigation in an airport sector. The inventive method and device make it possible to automatically calculate the points of intersection between the path of the flight plan and the zones having speed limitations all around an airport and calculate a speed profile conforming to these limitations. The inventive method and device also make it possible to use an automatic guidance automatically defining flight instructions corresponding to the calculated speed profile. Furthermore, the invention calculates predictions concerning the flight parameters. | 12-11-2008 |
20080312776 | METHOD AND APPARATUS FOR MANAGING FLIGHT PLANNING - A computer implemented method, apparatus, and computer usable program code for displaying flight plan data. First level flight plan data is displayed and user input is received selecting a selection of a portion of the first level flight plan data. In response to receiving the selection of the portion of the first level flight plan data, second level flight plan data is displayed, wherein the second level flight plan data displayed is used to derive the selected portion of the first level flight plan data selected by the user input. | 12-18-2008 |
20080312777 | Automatic Strategic Offset Function - Embodiments of methods and systems for providing an automatic strategic offset function are disclosed. In one embodiment, a method for enhancing the collision avoidance capability of an aircraft includes determining a flight plan, determining a boundary for the flight plan, generating a variable offset from the flight plan that is within the boundary, the variable offset including a lateral offset distance, and navigating an aircraft based on the variable offset. | 12-18-2008 |
20080312778 | SERVER DESIGN AND METHOD - A communication system for a vehicle includes a server that includes a real time operating system, at least one cabin function application that runs on the real time operating system, and at least one in-flight entertainment application that runs on another operating system on top of the real time operating system. Thus, an in-operation entertainment system is capable of providing audio and/or visual content to a large number of locations in a cabin of the vehicle, and a cabin function system is capable of providing various cabin applications, e.g., lighting level control, attendant calling, air conditioning control, etc. at different locations in the vehicle cabin in a manner that is isolated and prioritized over the entertainment system. | 12-18-2008 |
20080319590 | Systems for announcing the health of ball screw actuators and ball recirculation - A method of determining variations in operating characteristics of a mechanical system having a rotatory mode of operation and bearing balls entrained within a bearing balls recirculation system. There are provided the steps of first monitoring operating impulses generated by the mechanical system during a first interval of operation; first analyzing the operating impulses obtained during the first interval to determine the intensity and frequency of the operating impulses; first correlating the operating impulses obtained during the first interval to corresponding angular positions of the rotatory mode of operation; and first producing a first record of the intensity and frequency of the operating impulses obtained during the first interval correlated to the corresponding angular positions of the mechanical system. The health of bearing balls within the recirculation system is determined by monitoring the vibration characteristic of the recirculation system, which is correlatable to the specific bearing balls. | 12-25-2008 |
20090005916 | Systems and methods for communication, navigation, surveillance and sensor system integration in a vehicle - A system and method are provided for facilitating substantially seamless interface between individual component systems for sensor fusion, data exchange, and communication across a broad spectrum of component systems in a vehicle without implicating hardware or software upgrade within individual legacy systems and/or sensors. A universal translator is provided to interface between individual system components that exchange data in a seamless manner between legacy data formats and specific data formats advantageously employed by newly-developed, procured and installed individual component systems. One or more of an analog, digital or serial communications gateway network between one or more of vehicle control components and installed communication, navigation, surveillance and/or sensor sub-components and/or systems provides substantially seamless integration between such systems regardless of the individual data format and exchange capabilities to which the individual systems or sub-components may be designed. | 01-01-2009 |
20090005917 | System and method of carbon monoxide and fire detection and protection - A carbon monoxide and fire detection system and method are provided for vehicles, particularly light aircraft, which includes CO and smoke/heat detectors located in or near the pilot cabin that, in the event unsafe levels of CO is detected in the cabin or a fire is detected in the engine compartment, an electronic signal from the respective detector causes the heated ram-air and fresh-air control box valves to open or close to restrict heated air contaminated with CO and allow fresh-air into the cabin in the case of CO detection, or closing both valves thereby restricting a fire from entering the cabin through the heated ram-air or fresh air vents, as the case may be. | 01-01-2009 |
20090005918 | METHOD FOR OPTIMIZING THE EXIT OF AN AIRCRAFT IN A HOLDING CIRCUIT - The method of optimizing the exit of an aircraft traversing for a known duration (D) a holding circuit forming a racecourse comprising two parallel branches of the same distance, the branches being traversed in a first time (t | 01-01-2009 |
20090012657 | AUTONOMOUS OUTER LOOP CONTROL OF MAN-RATED FLY-BY-WIRE AIRCRAFT - The present invention is directed to a control system for use on a fly-by-wire (FBW) aircraft. The system includes a controller coupled to the FBW aircraft. The controller is configured to generate a plurality of simulated pilot control signals from at least one aircraft maneuver command. The plurality of simulated pilot control signals are generated in accordance with a predetermined control law. The at least one aircraft maneuver command is derived from at least one command telemetry signal received from a remote control system not disposed on the FBW aircraft. The plurality of simulated pilot control signals are configured to direct the FBW aircraft to perform an aircraft maneuver in accordance with the at least one aircraft maneuver command. | 01-08-2009 |
20090012658 | CONTROL SURFACE FAILURE DETECTION FOR FLY-BY-WIRE AIRCRAFT - A flight control system which detects a failure of a flight control surface and performs at least one action in response to the detected failure. | 01-08-2009 |
20090012659 | Manual Human Interfaces to Electronics - In accordance with one embodiment of the present disclosure, a method for controlling an aircraft by a hands on throttle-and-stick (HOTAS) includes selectively connecting, by the HOTAS, two interfaces of a controller for the aircraft. The selective connection is made through one of a plurality of possible paths. Each path has an expected respective voltage drop within a predetermined range. The selected one of the possible paths connecting the two interfaces is determined by determining an actual voltage drop associated with the selected path. A control operation for the aircraft is effected by the controller based on the determined selected path. The method reduces the number of required electrical connections. | 01-08-2009 |
20090012660 | Air Traffic Control - An air traffic control system, for use by a controller controlling multiple aircraft, comprising a processor, an input device and a display device, further comprising: trajectory prediction means for calculating a trajectory for each aircraft, for inputting aircraft detected position data, and for recalculating the trajectories based on said position data, and conflict detection means for detecting, based on the trajectories, future circumstances under which pairs of aircraft violate predetermined proximity tests, and for causing a display on the display device indicating said circumstances, further comprising means for inputting instruction data corresponding to instructions issued by the controller to an aircraft, and in which the proximity indication means is arranged to use a first proximity test and a second, more restrictive, proximity test; and in which the system is arranged to display a symbol representing pairs of aircraft which violate the second test in a first display mode, and those which violate the first set but not the second set in a second display mode, and in which the system is arranged, on input of a said instruction by a controller in relation to a pair of aircraft, to change the display mode of the symbol for said pair from the second mode to a third mode indicating that no further action is necessary. | 01-08-2009 |
20090018713 | SYSTEM FOR AIDING THE TAXIING OF AN AIRCRAFT - The invention relates to an integrated system carried onboard the aircraft used during taxiing or air/ground and ground/air transitions whose final objective is assistance to the crew in collaboration with the ground control authority. The system groups together a set of devices for mapping | 01-15-2009 |
20090018714 | METHOD AND DEVICE FOR CONTROLLING THE THRUST OF A MULTI-ENGINE AIRCRAFT - The device ( | 01-15-2009 |
20090030563 | Systems And Methods For Providing Localized Heat Treatment Of Metal Components - Systems and methods for defining information provided by aircraft are provided. An exemplary method, involving an aircraft that is operative to provide information in a first report format, includes: communicating information corresponding to a second report format definition to the aircraft, wherein the information corresponding to the second report format definition is received at the aircraft via wireless communication; and receiving, from the aircraft, information complying with the second report format definition. | 01-29-2009 |
20090030564 | METHOD AND APPARATUS FOR MANAGING INSTRUMENT MISSED APPROACHES - A computer implemented method, apparatus, and computer usable program code for managing missed approaches to runways. In one advantageous embodiment, an event requiring missing an approach to a runway by an aircraft is monitored for, while the movement of the aircraft along a route is being controlled by a flight management system. Responsive to detecting the event, a location of the aircraft is identified to form an identified location. The identified location of the aircraft is compared to a plurality of waypoints for a plurality of missed approach routes to identify an active waypoint in the plurality of waypoints closest to the aircraft to form an identified waypoint. A missed approach route from the plurality of missed approach routes associated with the identified waypoint is executed for the aircraft. | 01-29-2009 |
20090030565 | METHODS OF DETECTING MISALIGNMENT OF POINTS BELONGING TO AN AIRCRAFT FLIGHT PLAN - A method of detecting the misalignment of a first point ( | 01-29-2009 |
20090037034 | VEHICLE PERFORMANCE MONITORING SYSTEM WITH MULTI-LEVEL CACHING - A system and method for monitoring vehicle performance including multi-level caching. The system includes a vehicle portion with sensors, a vehicle caching data server, and a wireless transceiver and a monitoring station portion with monitoring workstations, a monitoring caching data server, and a wireless transceiver. The monitoring caching data server receives and aggregates requests for vehicle performance data from the monitoring workstations based on request priority and available bandwidth. The vehicle caching data server stores vehicle performance data from the sensors and selectively transmits a subset of the vehicle performance data to the monitoring caching data server in response to aggregate requests. | 02-05-2009 |
20090037035 | AIRCRAFT GAS TURBINE ENGINE BLADE TIP CLEARANCE CONTROL - A method and system adjusts blade tip clearance between rotating aircraft gas turbine engine blade tips and a surrounding shroud in anticipation of and before an engine command that changes an engine rotational speed. The method may include determining when to begin adjusting the tip clearance by expanding or contracting the shroud before the engine command and may be based on monitored aircraft and/or aircraft crew data indicative of the engine. The aircraft and/or aircraft crew data may include communications between aircraft crew and air traffic control authorities or air traffic control surrogates. Determining when to begin adjusting the tip clearance may include using learning algorithms which may use the aircraft gas turbine engine's operating experience and/or operating experience of other jet engines on an aircraft containing the aircraft gas turbine engine and/or on other aircraft. | 02-05-2009 |
20090037036 | Automatic Control Systems for Aircraft Auxiliary Power Units, and Associated Methods - Systems and methods for operating aircraft power systems are disclosed. A power system in accordance with one embodiment of the invention includes an aircraft auxiliary power unit and a controller coupled to the aircraft auxiliary power unit, with the controller being configured to automatically stop the auxiliary power unit while the auxiliary power unit is functioning normally. The controller can also be configured to automatically start the auxiliary power unit in-flight when power supplied or expected to be supplied to a subsystem of the aircraft has a non-zero value at or below a threshold value. The controller may also be configured to start the auxiliary power unit when a load or expected load on the subsystem meets or exceeds a threshold value. | 02-05-2009 |
20090048722 | COMPOUND AIRCRAFT CONTROL SYSTEM AND METHOD - The Invention is a control system for a compound aircraft. A compound aircraft has features of both a helicopter and a fixed wing aircraft and provides redundant control options. The control system allows an authorized person to select any of plurality of operational objectives each of which is designed to achieve any particular command. | 02-19-2009 |
20090055034 | INERTIAL NAVIGATION UNIT PROTOCOL CONVERTER - A protocol converter that translates the ARINC-429 protocol output of an Inertial Navigation System to the National Marine Electronics Association | 02-26-2009 |
20090062972 | Systems and Methods for Presenting and Obtaining Flight Control Information - Systems and methods for presenting and obtaining flight control information are disclosed. In one embodiment, information corresponding to a vertical motion of the aircraft can be displayed between information corresponding to a lateral motion of the aircraft and information corresponding to an airspeed of the aircraft. The information displayed can include a current mode for controlling the motion of the aircraft, a current target to which the aircraft is being directed and, at least proximate to both the current mode and the current target, a subsequent target to which the aircraft will be directed after attaining the current target. | 03-05-2009 |
20090069957 | UNMANNED HELICOPTER - GPS devices (GPS receivers and corresponding GPS antennas) for detecting a location of an airframe are provided. An autonomous control section (e.g., an autonomous control box) including a data communication device for communicating with the ground and a control board having a built-in control program is provided. An unmanned helicopter flies depending on airframe data such as an attitude and a speed of the airframe, engine speed, and a throttle angle and flight data such as a location and a direction of the airframe. The autonomous control section is provided with a plurality of different type of GPS devices. | 03-12-2009 |
20090069958 | SYSTEME DE FREINAGE DIFFERENTIEL - A braking system for the landing gear of an aircraft, which landing gear includes a bogey containing at least four wheels, each equipped with a brake, with the bogey having at least two axles that are connected to the aircraft by a telescoping strut, wherein when the aircraft makes a low-speed turn around a center of rotation, the straight line linking the center of rotation of the turn to the barycenter of the landing gear does not pass between the front wheels and the rear wheels of the landing gear which system further includes means for applying differential braking between the front wheels and the rear wheels of the landing gear. | 03-12-2009 |
20090076668 | Method and apparatus for providing power in an aircraft to one or more aircraft systems - A method and apparatus is disclosed in which an aircraft system such as the landing gear system or braking system is operated at least partially under power provided by a generator driven by the wheels of the landing gear. | 03-19-2009 |
20090093918 | Control Arrangement - An aerospace control arrangement comprising a control unit connected to a plurality of connecting node sets, each connecting node set having associated therewith a plurality of connecting nodes, and each node having associated therewith at least one effecter and/or sensor, resulting in at least some of the nodes being connected to the control unit in a fault isolated star, point to point, arrangement. | 04-09-2009 |
20090105892 | TELEMETRY ANALYSIS SYSTEM NETWORKED DATA ACQUISITION SYSTEM - The present invention is, in its various aspects and embodiments, a method and apparatus for use in acquiring telemetry regarding an airborne vehicle. In one aspect, the processing of acquired telemetry data is distributed to the points of acquisition rather than at the host station. In another aspect, various points on the telemetry acquisition system employ a common network interface through which the telemetry acquisition stations communicate acquired telemetry data to the control station. In still another aspect, the invention also includes a TDP/IP protocol for communicating between stations. Still other aspects and embodiments are disclosed and claimed. | 04-23-2009 |
20090112377 | System and Method for Virtual Information - A system for providing information to at least one passenger onboard a mobile platform (such as a train, marine vessel, aircraft or automobile) is provided. The system includes a display device that displays the information. The system also includes a source of user input coupled to the display device that enables the at least one passenger to request the information. The information includes at least galley information. The system further includes a galley control module that generates galley data that includes at least one food service item available onboard the mobile platform, and a graphical user interface module that displays the at least one food service item available onboard the mobile platform to enable the at least one passenger to select at least one of the at least one food service item. | 04-30-2009 |
20090112378 | System and Method for Aircraft Interior Annunciator - A system for an interior annunciator onboard a mobile platform (such as a train, marine vessel, aircraft or automobile) is provided. The system includes at least one speaker onboard the mobile platform. The system also includes a flight management control module that generates flight management data that indicates at least one status of an operation of the mobile platform. The system further includes an auditory control module that generates nonverbal auditory data based on the at least one status of the operation of the mobile platform. The nonverbal auditory data is broadcast by the at least one speaker to communicate the at least one status of the operation of the mobile platform to at least one passenger onboard the mobile platform. | 04-30-2009 |
20090112379 | Method and Arrangement for Providing a Fault Diagnosis For At Least One System - The present invention provides a method for providing a fault diagnosis for at least one system, in particular of an aircraft. The method comprises: (a) providing a number N | 04-30-2009 |
20090118874 | Systems and methods for controlling aircraft electrical power - Systems and methods for controlling aircraft electrical power are disclosed. A system in accordance with one embodiment includes an electric motor, an aircraft load coupled to the electric motor and powered by the electric motor, and a motor controller coupled to the electric motor to vary an output of the electric motor. The motor controller is changeable among a fixed number of preset controller modes, with individual controller modes corresponding to an operation mode of the aircraft and a non-zero output level of the electric motor. In further embodiments, motor controllers can be substituted for each other, e.g., in the event one motor controller becomes unoperational. | 05-07-2009 |
20090118875 | Systems and methods for coordination of entities and/or communicating location information - Systems and methods that may be employed to communicate location information between two or more aerial vehicles or other types of vehicles or other entities, and/or that may be used to facilitate coordinated operations of two or more such entities. In one example, an aerial vehicle may be kept aware of one or more location (e.g., longitude, latitude, etc.) and/or flight characteristics (e.g., altitude, directional heading, airspeed, attitude, etc.) of one or more other adjacent aerial vehicles, and each such aerial vehicle may use that location information to adjust its flight path to maintain a safe sphere of empty airspace around itself. | 05-07-2009 |
20090125164 | Integrated electronic module for visualizing digital instruments on a display - An electronic control unit includes in combination: a data collection element form sensors and instruments existing on board of the transport device, a collected-data processing element, a data storage element, a graphic display element, a radio communication element, and an input/output pilot interface element. The storage element includes a removable or fixed memory card. | 05-14-2009 |
20090125165 | METHOD AND DEVICE FOR PILOTING A PITCHING AIRCRAFT - The invention relates to a method and device for piloting a pitching aircraft. The inventive device ( | 05-14-2009 |
20090125166 | ACTIVE USER INTERFACE HAPTIC FEEDBACK AND LINKING CONTROL SYSTEM USING EITHER FORCE OR POSITION DATA - A system and method are provided for supplying haptic feedback to, and for electronically linking, pilot and co-pilot user interfaces. The user interface haptic feedback and linking are implemented using either force or position data. If the force or position data become unavailable, then position or force data, respectively, are used to implement the user interface haptic feedback and linking. | 05-14-2009 |
20090132102 | ACTUATOR CONTROL REDUCING THE LEVEL OF VIBRATION OF AN ASSOCIATED FLEXIBLE STRUCTURE - The aim of the method of controlling at least one mechanical system exhibiting at least one flexible structure element and at least one actuator or group of actuators is to reduce the level of vibrations of said element while controlling the actuator or group of actuators in such a way as to achieve at least one objective assigned to the mechanical system. The control consists of increments having to be carried out at a sampling period T, each of the increments being constant in amplitude in a sampling time interval extending between two successive sampling instants and each of the increments being applied during a duration which is less than or equal to the sampling period T. In each sampling interval, at least one of the initial and final instants of application of the increment is modified by adding a variable, random or pseudo-random, temporal deviation dT. | 05-21-2009 |
20090132103 | SYSTEM FOR SECURING AN AIRCRAFT FLIGHT PLAN - The system for securing an aircraft flight plan has a flight management system delivering: a flight plan and points comprising passage setpoints in terms of speed, altitude and time; an avionics computer; at least one resource for storing environmental data constituting a hazard for the aircraft; a performance model of the aircraft defining limiting flight conditions according to the performance capabilities of said aircraft; at least one resource for processing the aircraft's avoidance trajectories. It makes it possible, based on a sampling of points of the flight plan, to calculate a set of avoidance trajectories and correlate them with the environmental data in order to detect the engagement points requiring a corrective maneuver. | 05-21-2009 |
20090138138 | IMAGING AND DISPLAY SYSTEM TO AID HELICOPTER LANDINGS IN BROWNOUT CONDITIONS - An imaging and display system provides helicopter pilots with an unobstructed display of a landing area in a brownout or whiteout condition by capturing a high resolution image of the landing area prior to obscuration. Using inertial navigation information from the aircraft or an independent system, the system transforms the image to a desired viewpoint and overlays a representation of the helicopter's current position relative to the landing area. The system thus greatly improves orientation and situational awareness, permitting safe and effective operation under zero visibility brownout conditions. | 05-28-2009 |
20090138139 | TECHNICAL DATA NAVIGATION SYSTEM AND METHOD - The present invention is directed to a technical data navigation system and method that provides a single point of access search, retrieve and aggregate vehicle post delivery technical data via a lightweight three-dimensional (3D) navigational interface. The system and method provide for a streamlined process of virtually locating and identifying parts on a vehicle. The system and method further provide for a single point for interaction of delivering 3D simulations. | 05-28-2009 |
20090138140 | VEHICULAR LINEAR SENSOR SYSTEM - Vehicular sensor systems are provided. The vehicular sensor systems includes a support, first, second, and third sensors, and a support actuator. The first sensor is coupled to the support and configured to rotate about a first sensor axis. The first sensor has a first field of detection with a first central axis. The second sensor is coupled to the support and configured to rotate about a second sensor axis. The second sensor has a second field of detection with a second central axis. The third sensor is coupled to the support and configured to rotate about a third sensor axis. The third sensor has a third field of detection with a third central axis. The support actuator is coupled to the support and configured to rotate the support about a support axis. The first, second, and third central axes are substantially within a plane. | 05-28-2009 |
20090138141 | VEHICLE HEALTH MONITORING SYSTEM ARCHITECTURE FOR DIAGNOSTICS AND PROGNOSTICS DISCLOSURE - A health monitoring system for a vehicle system includes an operational support system including a plurality of managers and a decision support module. Each manager corresponds to a different sub-system of the vehicle system, and comprises a plurality of reasoners and a fusion block. Each reasoner is configured to obtain data and provide preliminary output regarding a different component of the sub-system based on the data. The fusion block is coupled to the plurality of reasoners, and is configured to receive the preliminary output and generating manager output based on the preliminary output. The decision support module is coupled to the plurality of managers, and is configured to receive the manager output and provide a decision support output based on the manager output. | 05-28-2009 |
20090143924 | SYSTEMS AND METHODS FOR ARBITRATING SENSOR AND ACTUATOR SIGNALS IN A MULTI-CHANNEL CONTROL SYSTEM - Systems and methods are provided for arbitrating sensor and actuator signals in various devices. One system includes input/output (I/O) circuitry, redundant computation circuits coupled to the I/O circuitry, and an arbitration circuit coupled between the I/O circuitry and the redundant computation circuits. The I/O circuitry is configured to be coupled to multiple non-redundant systems, and the redundant computation circuits are configured to be coupled to one of multiple system buses. One such device is an aircraft including multiple non-redundant systems and a plurality of system buses that are configured to transmit redundant messages to the non-redundant systems. A method includes receiving notice that redundant control signals have been received by multiple computation circuits, determining the health of each computation circuit, selecting a computation circuit from which to receive a control signal based on its health level, and transmitting the control signal from the selected computation circuit to I/O circuitry. | 06-04-2009 |
20090143925 | ROBUST CONTROL EFFECTOR ALLOCATION - Method and apparatus is disclosed which allocates the execution of a commanded vehicle maneuver among the vehicle's control effectors capable of affecting such maneuver, with consideration given to the possible nonlinear and/or non-monotonic effects each control effector's displacement may have on the vehicle and on each other's performance. | 06-04-2009 |
20090143926 | Method and apparatus for tracking center of gravity of air vehicle - The method and apparatus for tracking a center of gravity (COG) of an air vehicle provides a precise calculation and updating of the COG by disposing a plurality of acceleration measuring devices on a circumference of one or more rings in a manner that establishes redundancy in acceleration measurement. A multivariable time-space adaptive technique is provided within a high speed digital signal processor (DSP) to calculate and update the position of the COG. The system provides the capability of executing a procedure that reduces dispersion in estimating angular velocities and lateral accelerations of a moving vehicle and corrects the vehicle's estimated angular velocities and lateral accelerations. In addition, a consistency check of the measured values from the acceleration measuring devices is performed to assist in fault detection and isolation of a faulty accelerometer in the system. | 06-04-2009 |
20090150008 | METHOD AND DEVICE FOR GENERATING A SPEED FOR AN AIRCRAFT DURING A TAXIING - Method and device for generating a controlled speed for an aircraft rolling on the ground. | 06-11-2009 |
20090150009 | METHOD AND DEVICE CONCERNING THE TAXIING OF AN AIRCRAFT, WHICH IS AUTOMATIC AT LEAST IN PART - Method and device for the at least partially automatic driving of an aircraft rolling on the ground. | 06-11-2009 |
20090150010 | METHOD AND DEVICE FOR GENERATING A YAW SPEED ORDER FOR AN AIRCRAFT DURING A TAXIING - The device ( | 06-11-2009 |
20090150011 | METHOD AND DEVICE FOR GENERATING A SPEED PROFILE FOR AN AIRCRAFT DURING A TAXIING - A method and device for generating a speed profile for an aircraft rolling on the ground. | 06-11-2009 |
20090150012 | SYSTEM FOR PRODUCING A FLIGHT PLAN - A flight planning system includes one or more flight management system and a flight plan manager that constructs a flight plan according to static information from the flight management system. A flight management system that also constructs flight plans includes a flight plan manager that constructs a flight plan according to information stored in the flight management system. In constructing the flight plan, either flight management system may compute values of flight plan parameters, such as PNR, PET, ETOPS and LROPS, based on dynamic information related to the flight. On the ground, one of either type of flight management system is selected from a plurality thereof for producing a flight plan for a respective aircraft or aircraft model. | 06-11-2009 |
20090157233 | SYSTEM AND METHODS FOR AUTONOMOUS TRACKING AND SURVEILLANCE - A system and methods for autonomously tracking and simultaneously providing surveillance of a target from air vehicles. In one embodiment the system receives inputs from outside sources, creates tracks, identifies the targets and generates flight plans for unmanned air vehicles (UAVs) and camera controls for surveillance of the targets. The system uses predictive algorithms and aircraft control laws. The system comprises a plurality of modules configured to accomplish these tasks. One embodiment comprises an automatic target recognition (ATR) module configured to receive video information, process the video information, and produce ATR information including target information. The embodiment further comprises a multi-sensor integrator (MSI) module configured to receive the ATR information, an air vehicle state input and a target state input, process the inputs and produce track information for the target. The embodiment further comprises a target module configured to receive the track information, process the track information, and produce predicted future state target information. The embodiment further comprises an ownship module configured to receive the track information, process the track information, and produce predicted future state air vehicle information. The embodiment further comprises a planner module configured to receive the predicted future state target information and the predicted future state air vehicle information and generate travel path information including flight and camera steering commands for the air vehicle. | 06-18-2009 |
20090157234 | Regenerative integrated actuation system and associated method - A regenerative integrated actuation system and method are provided to efficiently supply power to a plurality of actuators and to make efficient use of power regenerated by the actuators. The system may include a plurality of actuators in communication with a power distribution system. Each actuator may include an energy storage element. The system may also include a controller for determining if a respective actuator is in a consumption mode or a regenerative mode. If in the consumption mode, the controller may determine whether the respective actuator should draw power from an energy storage element or from the power distribution system. Conversely, if in the regenerative mode, the controller may determine whether any excess power from the respective actuator should be provided to one of the actuators, such as to another actuator which is in the consumption mode or to the energy storage element associated with the respective actuator. | 06-18-2009 |
20090157235 | METHOD AND APPARATUS FOR MOVING A SWING TAIL CARGO DOOR ON AN AIRCRAFT - A computer implemented method, apparatus, and computer usable program code for a mobile tail support control system. An apparatus comprises a data processing system, an output device, a set of load sensors, a set of position sensors, and a computer program product executing on the data processing system. The output device is capable of generating signals for managing movement of a mobile tail support apparatus. The set of load sensors may be coupled to the data processing system and may be capable of detecting loads associated with a swing tail cargo door. The set of position sensors are coupled to the data processing system and detect a position of the mobile tail support apparatus relative to the swing tail cargo door. The computer program product may receive information from the set of load sensors and the set of position sensors and generate signals to manage the mobile tail support apparatus. | 06-18-2009 |
20090157236 | Intelligent system and method for spacecraft autonomous operations - The intelligent system for autonomous spacecraft operations includes an on-board Autonomous Operations subsystem integrated with an on-ground Web-based Remote Intelligent Monitor System (RIMS) providing interface between on-ground users and the autonomous operations intelligent system. The on-board Autonomous Operation subsystem includes an On-Orbit Checkout Engine (OOCE) unit and an Autonomous Tasking Engine (ATE) unit. Spacecraft Command Language (SCL) engine underlies the operations of the OOCE, ATE and RIMS, and serves as an executer of commands sequences. The OOCE uses the SCL engine to execute a series of SCL command scripts to perform a rapid on-orbit checkout of subsystems/components of the spacecraft in 1-3 days. The ATE is a planning and scheduling tool which receives requests for “activities” and uses the SCL scripts to verify the validity of the “activity” prior to execution, and scheduling the “activity” for execution or re-scheduling the same depending on verification results. Automated Mission Planning System (AMPS) supports the ATE operations. The ATE uses a priority schedule if multiple “activities” are to be executed. | 06-18-2009 |
20090157237 | MANUAL SELECTION OF THE ACTIVE REFERENCE OF A FLIGHT PLAN FOR THE GUIDANCE OF AN AIRCRAFT - The present invention relates to a method allowing a modification of the flight plan of an aircraft in a semi-automated manner. The invention presents the main advantage of affording the crew of an aircraft a method for aiding the rejoining of a flight plan requiring only a designation by an operator of the new active reference that he wishes to use for guiding the aircraft. | 06-18-2009 |
20090177338 | FAILSAFE REMOTE DATA CONCENTRATOR - A remote data concentrator receives signals from a plurality of sensors. Each of the sensors have their signals split between at least two flow paths, such that each of the sensors are provided with redundancy. | 07-09-2009 |
20090177339 | Optimization and Mechanization of Periodic Flight - The implementation of periodic flight for enhancing aircraft's endurance or range is described having at least two components in the periodic flight embodiments. The first component is the trajectory optimization which determines the optimal periodic trajectory (such as altitude, velocity and flight path angle) that produces maximal endurance or range for a given fuel. The second component is the periodic guidance law which mechanizes the optimal periodic trajectory. For certain aircraft, periodic flight improves that aircraft's endurance or range over steady state flight. | 07-09-2009 |
20090182462 | Method and system to accelerate aircraft wheels before touch-down - This invention improves the previous art to accelerate an aircraft's wheels before landing to avoid skidding in that it shows how to (1) provide adequate power by using the compressed air and gases of the jet engine, (2) rely on existing information from onboard systems to precisely control wheel spin and (3) integrate the propulsion device into the wheel structure. The invention minimizes the additional weight necessary to rotate the wheels of a landing aircraft, limits the aerodynamic impact and allows the use of existing tires without modifications. | 07-16-2009 |
20090198392 | APPARATUS, PROGRAM PRODUCT, AND METHODS FOR UPDATING DATA ON EMBEDDED CONTROL SYSTEMS - Embodiments of the present invention provide an augmentation apparatus, program product, and methods for providing updated mission control data to an embedded control system of an aircraft or other vehicle. This augmentation can include a mission system interface unit, a user interface unit, and a display unit. The mission system interface unit can interface with the embedded control system and can exchange data and control signals with the embedded control system. The user interface unit can couple to the mission system interface unit and the display unit to provide a user a direct interface with embedded control system and to supplement the displays of the embedded control system. | 08-06-2009 |
20090198393 | METHOD AND APPARATUS FOR LOADING SOFTWARE AIRCRAFT PARTS - A computer implemented method, apparatus, and computer usable program code for managing a software aircraft part. A computer implemented method identifies an aircraft from a set of target aircraft to form a target aircraft. Software for use in the aircraft is identified. A determination is made as to whether compatibility exists between the software and the target aircraft. The software aircraft part is created comprising the software and metadata relating usability of the software aircraft part in the target aircraft in response to a determination that compatibility exists between the software and the target aircraft. | 08-06-2009 |
20090204277 | Method of Estimating Atmospheric Data at Any Point of a Path of an Aircraft - The subject of the present invention is a method of estimating, at any point of a path of an aircraft, characteristics of the wind making it possible to take very close account of the winds to construct predictions of the times of passage and of the consumption of the aircraft along its flight plan, and this method is characterized in that it consists in collecting, around the trajectory of the aircraft, a grid of parameter values of winds at a predetermined number of points in space, in comparing these values to those deriving from space-time wind trend models, in selecting, path section by section, the most likely model, and in interpolating, for each section, the local characteristics of the wind of all the points of interest of the trajectory. | 08-13-2009 |
20090210103 | Controlling aircraft aerial movements, defeating icing on aircraft surfaces, aiding decontamination, and damping turbulence effects on aircraft by the method of micro-perforated airfoil coordinated precision flow management - A method is provided whereby airplanes or any device with the functionality and usefulness of an airplane may be controlled without the use of any traditional effectors, such as flaps, rudders, ailerons, spoilers, and all like hinged, moveable airfoils attached to a wing or a fuselage. The means of controlling such airplanes while in flight will be by controlling the laminar air flow over all lifting surfaces so as to vary the amount and quality of the lift provided. All lifting surfaces on the airplane will be divided into dozens, hundreds, or thousands of small zones, each of which can be readily controlled by a central flight computer and each of which is capable of modifying its immediate airflow condition, whether that be laminar flow or some particular degree and variety of local eddy current. Summing over all the inputs of conditions above the multitude of zones, the central flight computer will possess algorithms and programs suitable to effect any desired change in attitude, altitude, orientation, and course of the airplane that is desired. | 08-20-2009 |
20090210104 | PROCESS AND DEVICE FOR DIAGNOSTIC AND MAINTENANCE OPERATIONS OF AIRCRAFT - The object of the invention is a method and a device for filtering diagnostic messages obtained from a plurality of elements of a system, each of these elements comprising diagnostic means capable of detecting a failure and of transmitting a message comprising at least one failure indication. The state of at least certain elements of the said plurality of elements is represented by a model of state. After at least one failure message has been received, this message is filtered according to the failure indication that it contains and according to the model of state. In response to the filtering step, the model of state is updated according to the failure indication or the message is rejected. The filtering step is advantageously based on a propositional logic mechanism. | 08-20-2009 |
20090216391 | INERTIAL SIGNALS FOR FLIGHT CONTROL BACKUP MODE - A flight control system is provided that includes a reference system and flight control actuators. The reference system includes one or more sets of gyroscopes and accelerometers. At least one set of the gyroscopes and accelerometers are configured to provide a first output of a first set inertial signals for normal mode flight control and second output of a second different set of inertial signals for backup mode flight control. The flight control actuators are configured to be controlled by one of the first set of inertial signals and the second set of inertial signals. | 08-27-2009 |
20090216392 | VECTORED THRUSTER AUGMENTED AIRCRAFT - The Invention is a rotary-wing aircraft having at least two vectored thrusters that may be tilted from a horizontal to a vertical position and to positions intermediate between the horizontal and vertical positions. The two vectored thrusters are equipped with propellers having separately variable pitch. The two vectored thrusters also are equipped with vanes having selectable vane angles to direct separately the air flow from the two vectored thrusters. A control system detects the flight condition of the aircraft and selects vectored thruster control settings corresponding to the detected flight condition and consistent with predetermined control rules to provide lift, thrust, yaw moments and roll moments. | 08-27-2009 |
20090248224 | Integrated Air Navigation and Flight Control System - A method and a device for solving air traffic congestions, improve safety, and reduce faults to simplify cockpit equipment. The method serves the navigation of airplanes from port to port with the help of GPS signals. The navigation support is based on digital maps and position control by GPS signals, which GPS signals are corrected by GPS reference signals wherein depending on the present position and state of motion of the airplane the map is respectively the movement is selected automatically from a library and shown on a screen. | 10-01-2009 |
20090248225 | Apparatus For An Automated Aerial Refueling Boom Using Multiple Types Of Sensors - A system for automated control of a refueling boom coupled to a tanker aircraft is provided. The system includes: a first inertial measurement unit (IMU) providing inertial measurements for the tanker aircraft; a first GPS receiver providing a GPS location for a GPS antenna attached to the tanker aircraft; and a processor adapted to calculate a first inertial navigation state for the tanker aircraft through integration of the inertial measurements, the processor being further adapted to calculate a first inertial navigation state error relative to the GPS location and to filter the first inertial navigation state error and the first inertial navigation state based upon noise characteristics of the first IMU and the first GPS receiver to provide an updated inertial navigation state for the tanker aircraft, the processor being further adapted to control the refueling boom relative to a receiver aircraft based upon the first and updated inertial navigation states. | 10-01-2009 |
20090254230 | Distributed active vibration control systems and rotary wing aircraft with suppressed vibrations - An aircraft with at least one rotating machine creating troublesome vibrations, the aircraft comprised of an aerostructure, the aircraft including:
| 10-08-2009 |
20090259350 | PISTON ENGINE AIRCRAFT AUTOMATED PRE-FLIGHT TESTING - One embodiment is directed to a method for testing an aircraft prior to flight. The method includes receiving a user signal from a pre-flight test input source, the user signal indicating that a pilot of the aircraft has directed engine control circuitry, which is arranged to electronically control operation of a set of piston engines of the aircraft during flight, to begin testing the aircraft in an automated manner. The method includes, in response to the user signal, conducting a pre-flight test of the aircraft from the engine control circuitry. The method includes, upon completion of the pre-flight test, outputting a result of the pre-flight test from the engine control circuitry. | 10-15-2009 |
20090265049 | AIRCRAFT SYSTEM EMISSIONS AND NOISE ESTIMATION MECHANISM - A method for generating emissions estimations of an aircraft is provided. A plurality of aircraft parameters is gathered. A first parameter of the plurality of aircraft parameters is selected for a first model. The first model mathematically contributes to the formulation of a first emissions estimation. The first model is considered with a plurality of additional models in view of the plurality of aircraft parameters to obtain the first emissions estimation. The first emissions estimation is a composite representation of the first model and the plurality of additional models in view of the plurality of aircraft parameters. | 10-22-2009 |
20090276106 | Multiple Telemetry Stream Parsing and Reconstruction System - The invention generally relates to a telemetry system and method for parsing a set of archived telemetry streams for the purpose of reconstructing the data contained within the set of archived telemetry streams into a newly constructed set of telemetry streams. The newly constructed set of telemetry streams are used as a set of test driver data to evaluate performance in variety of ground based systems. The availability of test drivers produced by the preferred embodiment of the invention shortens the system development time line by allowing an evaluation of hardware and software changes ahead of the actual delivery of vehicle telemetry components, resulting in a reduction of overall program costs. | 11-05-2009 |
20090281683 | Developments in or relating to system prognostics - A method of mitigating the system-level effect of a fault detected in a vehicle system during a vehicle mission, the method comprising: using a processor to automatically prognose the system-level effect of said fault in terms of the residual capability of the vehicle system during the remainder of the mission, on the basis of predetermined stored data; using a processor to automatically generate a corresponding set of alternative reversionary or investigative action plans for mitigating said system-level effect during the remainder of the vehicle mission, on the basis of said prognosis; submitting the set of alternative reversionary action plans to a decision-making authority for determination by the decision-making authority of a preferred one of the reversionary action plans suitable for achieving a mission objective; and using a control unit, operably connected to the vehicle system, to implement the preferred reversionary action plan in accordance with said determination. | 11-12-2009 |
20090287364 | VISUAL AIRCRAFT SPACING TOOL - An air traffic display aid and method that uses parameters for defining a heading for an alpha approach and a beta approach. These can be intersecting or converging runways, dependent or independent parallel runways or airways in en-route configurations. A target reference point is determined in dependence upon the alpha and beta approaches. And an image reference point is determined in dependence upon at least one of the target reference point, a difference between the headings, a characteristic of the beta approach and an offset. Single target mirror ghosting, in-trail ghosting on demand, associated configurations and user selectable resynchronization spacing is also supported. | 11-19-2009 |
20090292405 | WING-BODY LOAD ALLEVIATION FOR AIRCRAFT - A computer implemented method, apparatus, and computer usable program product for symmetric and anti-symmetric control of aircraft flight control surfaces to reduce wing-body loads. Commands are sent to symmetrically deploy outboard control surfaces to shift wing air-loads inboard based on airplane state and speed brake deployment. Surface rate retraction on a wing with peak loads is limited to reduce maximum loads due to wheel checkback accompanied by utilization of opposite wing control surfaces to retain roll characteristics. Airloads are shifted inboard on a swept wing to move the center of pressure forward, thereby reducing the tail load required to perform a positive gravity maneuver. In a negative gravity maneuver, speed brakes are retracted, thereby reducing the positive tail load and reducing the aft body design loads. High gain feedback commands are filtered from wing structural modes above one hertz by a set of linear and non-linear filters. | 11-26-2009 |
20090292406 | METHODS AND SYSTEMS FOR REDUCING THE PHENOMENON OF STRUCTURAL COUPLING IN THE CONTROL SYSTEM OF AN IN-FLIGHT REFUELLING BOOM - A method for controlling a boom ( | 11-26-2009 |
20090292407 | SOLAR-POWERED AIRCRAFT WITH ROTATING FLIGHT SURFACES - A solar-powered aircraft having a rotating tail assembly and/or a fore assembly is provided. The tail and fore assemblies have solar cells mounted on their upper surfaces and are rotated during flight to track the sun. | 11-26-2009 |
20090299551 | SYSTEM AND METHOD FOR MULTIPLE AIRCRAFT LIFTING A COMMON PAYLOAD - A system and method are provided for controlling a plurality of aircraft to lift a common payload. The system comprises of multiple aircraft tethered to a common payload, where the group of said aircraft form a swarm that is controlled by a pilot station. Each said aircraft is autonomously stabilized and guided through a swarm avionics unit, which further comprises of sensor, communication, and processing hardware. At the said pilot station, a pilot remotely enters payload destinations, which is processed and communicated to each said aircraft. The method for controlling a multi-aircraft lifting system comprises of first inputting the desired location of the payload, and then determining a series of intermediary payload waypoints. Next, these payload waypoints are used by the swarm waypoint controller to generate individual waypoints for each aircraft; a flight controller for each aircraft moves the aircraft to these individual waypoints. | 12-03-2009 |
20090299552 | METHOD AND SYSTEM FOR AUTOMATICALLY MANAGING A CONVOY OF AIRCRAFT DURING A TAXIING - The system ( | 12-03-2009 |
20090306836 | Aircraft Emergency Handling - The present invention provides methods and apparatuses that reduce pilot workload and increase the performance and efficiency of the pilot's control of the aircraft. The present invention comprises methods and apparatuses for determining the presence and type of an emergency condition, for example by detecting corresponding sensor outputs or by accepting input from a pilot or a combination thereof; and then responding to that emergency by initiating a pre-determined set of actions specific to the determined emergency. Embodiments of the invention can include the ability to monitor engine conditions as well as control electrical functions such as the fuel boost pump, alternator field, battery contactor and other important electrical devices. Some examples described below assume a single-engine piston aircraft for ease of illustration. The invention can also be applied to multi engine and turbine powered aircraft as well. | 12-10-2009 |
20090306837 | Aircraft Exhaust Gas Temperature Monitor - A computer-implemented function monitors and displays exhaust gas temperatures (EGT) in a plurality of cylinders in an engine. The invention provides an easy way to read exhaust gas temperature on a specific cylinder, and to provide a means for leaning the engine while in a climb. Efficient leaning in a climb reduces fuel consumption and reduces the chance of harmful conditions that can lead to engine failure. | 12-10-2009 |
20090306838 | METHOD AND DEVICE FOR AIDING THE MAINTENANCE OF A SYSTEM - The invention relates to a method for aiding the maintenance of a system, the system comprising a set of networked elements, the system being accompanied by indications defining subsets of networked elements E | 12-10-2009 |
20090312891 | Conversion system fault management system for tiltrotor aircraft - The difference between a first position of a first pylon of a tiltrotor aircraft and a second position of a second pylon of the aircraft is prevented from becoming too large. An actuator position error for the first pylon is calculated from a difference between the first position and a commanded first position of the first pylon. An actuator position error for the second pylon is calculated from a difference between the second position and a commanded second position of the second pylon. An absolute value of the actuator position error for the first pylon is compared to the preset limit. If the absolute value of the actuator position error for the first pylon is greater than or equal to a preset limit, the actuator position error for the second pylon is calculated from the difference between the first position and the second position. | 12-17-2009 |
20090312892 | DISTRIBUTED ENGINE CONTROL SYSTEM - A distributed engine control system is provided. The engine control system includes first and second engine data concentrators. Each of the first and second engine data concentrators include a processor module, a signal conditioning module coupled to the processor module, a data transfer module coupled to the processor module, and a data bus coupled between the first and second engine data concentrators and a hydro-mechanical unit (HMU). | 12-17-2009 |
20090319097 | HAND CONTROLLER ASSEMBLY - A user input device for a vehicular electrical system is provided. The user input device includes a handle sized and shaped to be gripped by a human hand and a gimbal assembly within the handle. The gimbal assembly includes a first gimbal component, a second gimbal component coupled to the first gimbal component such that the second gimbal component is rotatable relative to the first gimbal component about a first axis, and a third gimbal component coupled to the second gimbal component such that the third gimbal component is rotatable relative to the second gimbal component about a second axis. | 12-24-2009 |
20090319098 | SYSTEM FOR DISPLAYING REQUIRED NAVIGATION PERFORMANCE ON A HORIZONTAL SITUATION INDICATOR - A display system is provided that renders a horizontal situation indicator that includes required navigation performance (RNP) and estimated position uncertainty (EPU) values rendered non-numerically and in a fairly intuitive manner. A processor receives at least data representative of a desired course of the aircraft, data representative of the RNP for the aircraft, and data representative of the EPU for the aircraft. The processor renders, on a display device, a horizontal situation indicator that includes an aircraft symbol representative of a top-down view of the aircraft, an RNP boundary graphic representative of at least one RNP boundary for the aircraft, and an EPU graphic representative of the EPU for the aircraft. The aircraft symbol is rendered at a position that is representative of actual aircraft position relative to the desired course, and the RNP boundary graphic is rendered at a position relative to the rendered aircraft symbol and comprises a shaded region that shades a portion of the display device. | 12-24-2009 |
20090319099 | COMPUTER MAINTENANCE SYSTEM FOR AN AIRCRAFT WITH REMOTE TERMINAL - The present invention relates to a computer maintenance system for an aircraft comprising a server hosting maintenance software and at least one access terminal. The system comprises a KVM switch over IP linked to said server. The terminal is adapted to connect to said switch by means of a TCP/IP connection and hosts a client application. Symmetrically, the switch hosts a server application, said applications being suitable for implementing a protocol for remotely accessing a video frame buffer. Each video frame is transmitted from the server application to the client application in the form of bitmap image data, uncompressed or else compressed by a lossless compression algorithm. | 12-24-2009 |
20090326736 | Relative navigation for aerial refueling of an unmanned aerial vehicle - A method and system for navigating an unmanned aerial vehicle (UAV) for aerial refueling is described. A system processor in the UAV receives navigation data from a tanker aircraft and calculates a plurality of relative navigation solutions with respect to the tanker aircraft. The system processor compares the plurality of relative navigation solutions to identify any inconsistent solutions. The inconsistent solutions are discarded and the system processor navigates the UAV in position for refueling using the remaining relative navigation solutions. | 12-31-2009 |
20090326737 | SMART HYBRID ELECTRIC AND BLEED ARCHITECTURE - An aircraft architecture may be designed to create an optimal balance between electric power and bleed power in order to match or improve current more electric architecture (MEA) performance while simplifying power extraction from the engines as well as simplifying the electrical system. Conventional aircraft architectures may use electric only ECS and cabin pressurization systems (so-called “no bleed” systems). Alternatively, older conventional aircraft may use strictly engine bleed air to provide power for ECS and cabin pressurization systems. The present invention, on the other hand, provides an architecture which may optimize the use of both engine bleed air and MEA designs to provide a system that may be simpler and potentially more reliable and available as compared to conventional aircraft architectures. | 12-31-2009 |
20090326738 | DEVICE FOR AIDING TO TAKE A DECISION CONCERNING THE ABILITY OF AN AIRCRAFT TO START A FLIGHT - The device ( | 12-31-2009 |
20090326739 | METHOD AND DEVICE FOR DETECTING OSCILLATORY FAILURES RELATED TO A SERVOCONTROL SUBSYSTEM OF AN AIRCRAFT CONTROL SURFACE - Method and device for detecting oscillatory faults relating to an aircraft airfoil slaving chain. | 12-31-2009 |
20090326740 | Methods for determining an initial AINS heading - Two methods for determining a best initial heading estimate for use in an AINS system, while recording position data values and in-motion data values, assigning incremental changes to indexed heading ψ | 12-31-2009 |
20100004799 | Systems and Methods for Alleviating Aircraft Loads with Plasma Actuators - Systems and methods for alleviating aircraft loads with plasma actuators are disclosed. A method for operating an aircraft in accordance with a particular embodiment includes receiving an input corresponding to an aircraft component structural response to an aerodynamic load. The method can further include, based at least in part on the input corresponding to the aircraft component's structural response, reducing the structural response to the aerodynamic load by activating at least one plasma actuator carried by the aircraft, in accordance with one or more activation parameters. | 01-07-2010 |
20100004800 | Method and system for resolving traffic conflicts in take-off and landing - A method and system for resolving existing and potential traffic conflicts that may occur during take-off and landing in aviation that includes means of monitoring movements on the runway, its approaches and environs to determine whether a conflict or potential conflict exists, means to resolve a conflict and to generate an output pertaining to this resolution. | 01-07-2010 |
20100010692 | Integrating avionics system with single event upset autonomous recovery - A novel system and method for detecting and recovering from single event upsets in integrating processing systems are presented. Two delta value processing lanes may be utilized to process raw data from inertial sensors. The output of the two processing lanes may be compared to detect the presence of an SEU. If an error is detected, a previously stored set of delta values may be utilized by the system. Additionally, the system may contain a temporary buffer to store calculated delta values in the event of a processor reset caused by an SEU or other error. The temporary buffer may store delta values accumulated during the processor reset and may furnish these stored delta values to the processor once it has finished resetting. The stored delta values may then be batch-processed and applied to system state values saved to memory prior to the processor reset. | 01-14-2010 |
20100017047 | Systems and methods for remote display of an enhanced image - A system for providing remote display of an enhanced image comprises at least one image source and a processing element. The processing element is capable of receiving data from the image source, creating an enhanced image with the received data, and transmitting the enhanced image via a wireless link to a display device capable of displaying the enhanced image. The processing element may create the enhanced image by stitching image data from at least two image sources having different fields of view, fusing image data from at least two image sources having different image modalities, or combining image data from at least one image source with synthetic image data. The processing element may be further capable of modifying at least one transmission characteristic based on a bandwidth of the wireless link. The transmission characteristic may be selected from the group comprising field of view, frame rate, resolution, and compression. | 01-21-2010 |
20100017048 | MODEL BASED SENSOR SYSTEM FOR LOADS AWARE CONTROL LAWS - A flight control system includes a model-based sensor system which estimates angular accelerations to control rotor system moment such that loads on the aircraft structure are reduced to thereby allow an aircraft structural envelope to more closely follow an aircraft service flight envelope. | 01-21-2010 |
20100017049 | Vehicle Health Management Systems and Methods - Systems and methods for managing the exchange of vehicle information between software modules with different safety importance. In one embodiment, a vehicle health management system includes a mission critical software module, a flight critical software module and a gatekeeper. The mission critical software module receives vehicle state information and provides it to the flight critical software module if the gatekeeper confirms the validity of the vehicle information. | 01-21-2010 |
20100023186 | FLY-BY-WIRE FLIGHT CONTROL SYSTEM WITH ELECTRONIC LEAD/LAG DAMPER ALGORITHM - An electronic lead/lag damper algorithm implemented as part of the fly-by-wire flight control system to minimize or eliminate mechanical lead/lag dampers of a rotary wing aircraft. The electronic lead/lag damper algorithm uses a cross-feed control methodology that band-pass filters pitch and roll rates and feeds back a signal to the lateral and longitudinal cyclic inputs to provide electronic stability to rotor lag modes. | 01-28-2010 |
20100030400 | AUTOMATIC SPEECH RECOGNITION SYSTEM AND METHOD FOR AIRCRAFT - A system and method which implement automatic speech recognition (ASR) and text-to-speech (TTS) programs to permit pilots, co-pilots, and other persons to more quickly and easily perform control and monitoring tasks on aircraft. The system may be used to automatically change the frequency of an aircraft radio when a pilot or co-pilot is instructed to do so by ATC. | 02-04-2010 |
20100030401 | FLIGHT DECK COMMUNICATION AND DISPLAY SYSTEM - A flight deck communication and display system ( | 02-04-2010 |
20100030402 | LIGHT MULTI-PURPOSE AIRCRAFT WITH A CONTROLLING INTEGRATED COMPLEX - A light multi-purpose aircraft with a controlling integrated complex comprises a fuselage ( | 02-04-2010 |
20100030403 | METHODS AND APPARATUS FOR AIRBORNE SYSTEMS - In various representative aspects, an airborne delivery system according to various aspects of the present invention comprises a container and an autorotating rotor system. The container may contain contents, and the rotor system facilitates control of at least a portion of the flight of the airborne system and the descent. Exemplary features may include a guidance system, for example to guide and control the airborne system, and a wing for gliding. | 02-04-2010 |
20100036547 | System and methods for on-board pre-flight aircraft dispatching - Systems and methods for providing pre-flight dispatching are disclosed. In one embodiment, a system for on-board dispatching of an aircraft includes a flight dispatching apparatus positioned within the aircraft that is configured to perform one or more flight dispatching tasks. A communications apparatus is configured to exchange wireless signals between the dispatching apparatus and one or more ground-based facilities. In another embodiment, a method of dispatching an aircraft includes designating a person to perform predetermined dispatching tasks, and establishing a wireless data connection between the aircraft and at least one ground-based facility. Information obtained from the at least one ground-based facility is then processed to perform the one or more dispatching tasks, and at least a portion of the processed information is communicated to the at least one ground-based facility using the wireless data connection. | 02-11-2010 |
20100042267 | PROGRAMMABLE REVERSE THRUST DETENT SYSTEM AND METHOD - A reverse thrust detent system for an aircraft includes a throttle quadrant having an intermediate reverse thrust detent position, a reverse thrust scheduling system interfacing with the throttle quadrant, at least one aircraft engine interfacing with the reverse thrust scheduling system and a programmable input interfacing with the reverse thrust scheduling system and adapted to receive an engine reverse thrust setting. The reverse thrust scheduling system is adapted to operate the at least one aircraft engine according to the engine reverse thrust setting responsive to actuation of the intermediate reverse thrust detent position of the throttle quadrant. A reverse thrust detent method for an aircraft is also disclosed. | 02-18-2010 |
20100042268 | APPARATUS, AND ASSOCIATED METHOD, FOR TRACKING AIRCRAFT STATUS - An apparatus, and an associated method, provides a visualization of an aircraft status relative to a scheduled airline timeline for the aircraft. Input information associated with the aircraft and operations associated therewith, are provided and detected. The input information is used to generate a timeline having one or more milestones and an aircraft icon. The timeline and the aircraft icon are together displayed by a displayer. The visualization is viewable by airline personnel, permitting their viewing of the visualization. | 02-18-2010 |
20100042269 | SYSTEM AND METHODS RELATING TO AUTONOMOUS TRACKING AND SURVEILLANCE - A method of protecting an asset using at least one unmanned vehicle. The method includes establishing a plurality of boundaries around the asset. The boundaries define edges of zones. The method further includes observing a target in a first one of the zones. The method further includes deploying the unmanned vehicle to a location in a vicinity of the asset and tasking the vehicle to perform a first defensive measure as long as the target remains in the first zone. If the target crosses a boundary from the first zone into a second one of the zones, where the second zone is more proximate to the asset than the first zone, the method further includes tasking the vehicle to perform a second defensive measure. | 02-18-2010 |
20100049377 | SENSOR AND ANTENNA ARRANGEMENT - An exemplary sensor for an aircraft includes a sensor mountable within an aircraft and operative to communicate wirelessly communications to a distributed aperture antenna. The sensor is operative to harvest energy from the aircraft to power the sensor. | 02-25-2010 |
20100049378 | METHOD AND DEVICE FOR ASSISTING IN THE PREPARATION AND MANAGEMENT OF MISSIONS IN AN AIRCRAFT - The invention in particular has as its object a method and a device for an aircraft for aiding in the preparation and management of missions. After a plurality of digital data has been received ( | 02-25-2010 |
20100049379 | METHOD AND DEVICE FOR ASSISTING IN THE DIAGNOSTIC AND IN THE DISPATCH DECISION OF AN AIRCRAFT - The invention has as its object in particular a method and a device for aiding in the diagnosis and in the decision on operation of an aircraft comprising means for detection of failures relating to the pieces of equipment thereof. After having received ( | 02-25-2010 |
20100049380 | METHOD AND SUPPORT DEVICE FOR AIDING IN THE PREPARATION AND MANAGEMENT OF MISSIONS IN AIRCRAFT - The invention in particular has as its object a method and a device for an operating center for aiding in the preparation and management of missions of an aircraft. After a plurality of digital data has been received ( | 02-25-2010 |
20100070109 | SYSTEM AND METHOD FOR DISPLAYING A DIGITAL TERRAIN - Methods and systems for displaying a digital terrain to a user of a vehicle are provided. First, second, and third actual terrain data points are received. The third actual terrain data point is between the first and second actual terrain data points. If the third actual terrain data point is above a line interconnecting the first and second actual terrain data points, the first actual terrain data point is modified such that the third actual terrain data point is not above a line interconnecting said modified first actual terrain data point and the second actual terrain data point. A digital terrain is displayed to the user of the vehicle. The digital terrain includes a first digital terrain data point corresponding to the modified first actual terrain data point. | 03-18-2010 |
20100070110 | METHODS AND SYSTEMS FOR INDICATING FUEL REQUIRED TO REACH A LOCATION - Methods and systems are provided for indicating on a display device whether a vehicle has sufficient fuel remaining to travel from a first location to a second location. An exemplary method involves determining the amount of fuel required for the vehicle to travel from the first location to the second location. If the amount of fuel required is greater than a threshold fuel value associated with the first location, the method displays a graphical representation of the second location on the display device using a first visually distinguishable characteristic. If the first amount of fuel is less than the threshold fuel value, the method displays the graphical representation of the second location on the display device using a second visually distinguishable characteristic. | 03-18-2010 |
20100070111 | SYSTEM FOR AERIAL DELIVERY OF FIRE RETARDANT - A system for launching, controlling and delivering in a preselected target pattern a plurality of low-cost, guided fire-retardant-containing vehicles, i.e., “smart water bombs” equipped with control surfaces sufficient to provide limited lift and maneuverability to respond to guidance command to place it at a selected GPS coordinate within a large footprint in time and space and to discharge its payload of fire retardant at a preselectable altitude in a very precise manner and dispersion pattern. A controller determines bombing patterns and timing for all bombs and trajectories for each guided bomb. Dynamic differential equations are used to determine location and time of release of the guided bombs to achieve the target while avoiding collisions among guided bombs and aircraft. | 03-18-2010 |
20100070112 | PROGRESSIVE TAKEOFF THRUST RAMP FOR AN AIRCRAFT - A method is presented for controlling thrust generated by aircraft engines. Engine thrust is controlled based on aircraft groundspeed and airspeed during the initial part of takeoff. Limiting thrust at low groundspeed during the initial phase of takeoff has significant benefits that reduce engine stress during this brief but critical phase leading to flight. Logical elements combine both groundspeed and airspeed in such a way that the operator perceives a smooth progressive thrust increase consistent with normal engine operation. | 03-18-2010 |
20100076623 | BRAKING PROCESS FOR AN AIRPLANE - An aircraft braking adaptation process is used to prevent rapid derotation of an aircraft causing damage to the front landing gear by formulating a braking command, applying the command to at least one brake, adapting the braking command by acquiring the aircraft trim and modifying the braking commands as a function of the aircraft trim. | 03-25-2010 |
20100082184 | DISPLAYING AIR TRAFFIC SYMBOLOGY BASED ON RELATIVE IMPORTANCE - A method and system is provided for displaying aircraft symbology. The method includes displaying ( | 04-01-2010 |
20100082185 | System and Method for Calculating Flight Predictions by Vertical Sections - The invention relates to a system and a method for calculating flight predictions of an aircraft in which an intermediate prediction horizon is defined between the flight phase and the leg. This horizon, that is called vertical section, is defined such that the limit conditions that are applicable to it, for example the target speed, target altitude, characteristic altitude and maximum end-of-section distance, are valid for the entire vertical section. Thus, it is not necessary, in calculations to check the compatibility of the flight parameters with the applicable constraints, to arbitrarily select the constraint that must be given priority. Furthermore, this intermediate level architecture allows for a greater modularity of the prediction management software and therefore a greater factorization of the developments and greater ease of maintenance. | 04-01-2010 |
20100087969 | Automated System with Deterministic Response Times - The invention relates to an automated system, for example an aircraft flight management system (FMS). If proposes harmonizing the response times of the FMS system between the various scenarios of one and the same family, as and when the product, and its usage context, changes. | 04-08-2010 |
20100094484 | INTEGRATING COMMUNICATION AND SURVEILLANCE - An aircraft control unit has modules for interfacing with various systems of an aircraft to integrate control of the systems. The modules include a communication module configured to be coupled to a communication system of the aircraft and a surveillance module configured to be coupled to a surveillance system of the aircraft. The aircraft control unit also includes a display screen for displaying information and a user interface usable to interact with the modules. Each of the modules is configured to display information on the display screen and to receive user input from the user interface. | 04-15-2010 |
20100094485 | Computation-Time-Optimized Route Planning for Aircraft - A process and system for the planning a cost-minimized aircraft flight route between a starting point and end point takes into account costs associated with the flight route, no-fly zones and flight corridors, and aircraft limitations. A raster set is determined which comprises topographical points between the starting and end points, and costs associated with the respective raster points are determined. N nodes are determined for each raster point of at least one subset of the raster set, such nodes being associated with approach directions of the raster point by the aircraft. Possible take-off directions of the raster point are defined, taking into account the minimum turning radius of the aircraft, as a function of the approach direction. A cost-minimized flight route is determined by means of a shortest path algorithm, taking into account only the k most cost-effective nodes (k04-15-2010 | |
20100100257 | Visual airport surface and terminal area data system - The invention supports the study of operations and provides a large data store of surface and terminal area operations, as well as means of analyzing and understanding that data. It fuses multiple surveillance and flight data sources to provide analysis functionality for both airborne and surface based flights. This provides a wider range of data to make intelligent categorization and derived data analysis decisions. The invention implements custom logic for matching flights to corresponding data messages by maintaining its own key mappings between data tables during import so that keys are unique to an installation and do not require sequences. This provides the ability to export datasets through the PostgreSQL dump utility and then import it into an existing database (using the PostgreSQL restore utility) without creating overlapping, duplicate or conflicting keys. XML based format is used and import and export features is that allow users to share these custom queries. | 04-22-2010 |
20100100258 | Method of Ergonomically Selecting a Reference Course/Radial for the Guidance of an Aircraft - The invention relates to a method and an associated device making it possible to avoid guidance command input errors by the crew. Since the course and the radial are linked by different relationships depending on whether the aircraft is approaching or moving away from a point, the procedures from air traffic control may be given either in course or in radial, and since the FMS system can also require the input of one of the two values, the number of possible different combination creates a situation of ambiguity that is prejudicial to the safety of the flight. To resolve this problem, the invention proposes a systematic display in text mode and/or in graphic mode of the input datum (course or radial) and of the other for verification by the crew. | 04-22-2010 |
20100100259 | FAULT DIAGNOSIS DEVICE AND METHOD FOR OPTIMIZING MAINTENANCE MEASURES IN TECHNICAL SYSTEMS - The present invention provides a fault diagnosis device for optimizing maintenance measures in a system, in particular a flying object. The diagnosis device has a storage unit for storing diagnosis rules, which each have a fault condition indicating the presence of a fault, and a fault conclusion formed by logical combinations of potential fault causes of the respective fault. Furthermore, a logic unit is provided, which logically combines those stored fault conclusions whose associated fault conditions are met and, on the basis of the combined fault conclusions, determines a logical diagnosis result having at least one fault cause hypothesis. A calculation unit subsequently calculates an occurrence probability for each fault cause hypothesis of the logical diagnosis result determined. | 04-22-2010 |
20100106346 | METHOD AND SYSTEM FOR MANAGING FLIGHT PLAN DATA - Method and systems for managing flight plan data associated with an aircraft are provided. A list of navigational entry selections (e.g., flight plan origins and flight plan destinations) is generated. Each of the navigational entry selections is associated with the aircraft (e.g., previously used). The list of navigational entry selections is displayed to a user of the aircraft. An indication of a selection of at least one of the navigational entry selections is received from the user. The navigational entry selections are generated, for example, based on navigational entries previously stored in a memory on-board the aircraft, a location of the aircraft, or a combination of the previous navigational entries and the location of the aircraft. | 04-29-2010 |
20100106347 | INDEPENDENT BRAKE CONTROL OF A COMMON AIRCRAFT GEAR - A brake control system for a landing gear of an aircraft is provided. The system includes a first control channel for providing brake control signals to one or more brakes on the landing gear, and a second control channel for providing brake control signals to another one or more brakes on the landing gear. At least one of the first control channel and the second control channel is configured to act as an executive in monitoring braking efforts applied by the one or more brakes as compared to braking efforts applied by the another one or more brake, and to cause the braking efforts of at least one of the one or more brakes or the another one or more brakes to be modified in an effort to equalize the braking efforts. | 04-29-2010 |
20100114406 | METHOD AND SYSTEMS FOR REQUIRED TIME OF ARRIVAL PERFORMANCE DISPLAY - A method and system for a required time of arrival (RTA) performance graphic display is provided. The system includes a processor programmed to receive a required time of arrival and a first visual display communicatively coupled to the processor. The first visual display includes an RTA graphic having a dial substantially symmetric about an axis, a first marker indicative of a current estimated time of arrival (ETA) at a predetermined waypoint, a second marker indicative of a value of the RTA relative to the current ETA value and a selected RTA time tolerance value, a first indication representing a first time the vehicle can attain the predetermined waypoint, a second indication representing a last time the vehicle can attain the predetermined waypoint, a third indication representing the uncertainty of the ETA in an early arrival direction, and a fourth indication representing the uncertainty of the ETA in a late arrival direction. | 05-06-2010 |
20100114407 | METHODS AND SYSTEM FOR TIME OF ARRIVAL CONTROL USING AVAILABLE SPEED AUTHORITY - Methods and a system for a vehicle control system using a reference time profile including an upper control bound and a lower control bound are provided. The system includes an input device configured to receive a required time of arrival at a waypoint and a processor communicatively coupled to said input device wherein the processor is programmed to generate a reference time profile using a first speed profile up to an intermediate control point and a second speed profile between the intermediate control point and an RTA waypoint. The system also includes an output device communicatively coupled to the processor wherein the output device is configured to transmit a speed control signal based on the reference time profile to a vehicle speed control system. | 05-06-2010 |
20100114408 | MICRO AERIAL VEHICLE QUALITY OF SERVICE MANAGER - The present invention provides methods and systems for adjusting video quality outputted by an aerial vehicle to manage the data stream bandwidth to match the needs of each mission segment. A mission segment is monitored in order to determine a preferred video quality of service. A quality of service is set based on the monitored mission segment. The quality of service is selectively altered based on a change of at least one of a mission segment or an environmental condition. | 05-06-2010 |
20100114409 | METHOD OF INSPECTING THE INTEGRITY OF AN AVIONICS SYSTEM, AND AN INSPECTION DEVICE FOR IMPLEMENTING SAID METHOD - A method of inspecting the integrity of an avionics system ( | 05-06-2010 |
20100114410 | METHOD OF ENSURING THE INTEGRITY OF FLIGHT DATA AND A SYSTEM FOR IMPLEMENTING SAID METHOD - A method of transferring and processing flight data of an aircraft including recording the aircraft flight data in an onboard avionics system in a digital format so as to obtain digital data, the flight data including safety impact flight data and flight data having no recognized effect on safety. The method further includes recording at least the safety impact flight data in the onboard avionics system in an additional format dissimilar to the digital format so as to obtain additional flight data, storing the digital data and the additional flight data separately, transferring the digital data and the additional flight data to a monitoring computer on the ground, displaying the digital data on a screen in the form of display digital data, and transferring the digital data and the additional flight data to a complementary interpretation unit so as to generate one of display data and print data relating to the additional flight data. | 05-06-2010 |
20100125378 | AUTOMATIC THROTTLE ROLL ANGLE COMPENSATION - A method, apparatus, and computer program product for adjusting a thrust for an aircraft. A level of thrust is dynamically identified using a drag on the aircraft needed to substantially maintain a speed of the aircraft in a turn to form an identified level of thrust during turning of the aircraft. The turn of the aircraft is performed using the identified level of thrust. | 05-20-2010 |
20100125379 | Device Allowing Improvement in Maintenance Procedures for Onboard Equipment - The present invention relates to the field of aiding ground maintenance of an aircraft. More particularly, the invention consists of a portable access terminal intended to aid maintenance, commonly designated by the acronym PMAT for Portable Maintenance Access Terminal. | 05-20-2010 |
20100125380 | Method And Device For Fault Detection In The Load Path Of A Spindle Actuator - A method and a device for fault detection in the load path of a spindle actuator which is provided for actuating an aerodynamically active surface, in particular a high-lift flap of an aircraft, wherein the spindle actuator has a redundant load path which is formed by a spindle and a secondary connection which are connected rotationally fixedly to one another on the driven side and are coupled to the surface to be actuated and which are assigned separate load paths on the drive side, whereof the primary load path contains a primary spindle which is driven by a motor and can be fixed in its rotational movement by a primary brake, and the secondary load path contains the secondary inner connection, which is in particular arranged concentrically in the primary spindle, which can be fixed in its rotational movement by a secondary brake, in which output signals representing the turning position of the spindle, which are generated by means of at least one turning position sensor which is coupled to the primary spindle on the drive side, are detected and evaluated, wherein: fixing the secondary connection in its rotational movement is achieved by means of the secondary brake; the redundant load path is put under load, when the primary brake is released, the load being applied via a predefined torque by the motor as far as the secondary brake is fixing the secondary connection; and the detection of a fault is evaluated when a change in the turning position, which lies outside the tolerance range predefined for an intact spindle actuator, is detected at the turning position sensor coupled to the primary spindle. | 05-20-2010 |
20100131123 | INPUT/STEERING MECHANISMS AND AIRCRAFT CONTROL SYSTEMS - Input/steering mechanisms and aircraft control systems are provided. In an embodiment, by way of example only, an input/steering mechanism is provided for use with an aircraft control system. The input/steering mechanism includes a handlebar, a first panel extending from the handlebar, and a first portion of an alphanumeric keyboard disposed on the panel and adapted to receive a manual input from a user and to transmit an output signal to the aircraft control system in response to the manual input. | 05-27-2010 |
20100131124 | METHODS AND SYSTEM FOR TIME OF ARRIVAL CONTROL USING TIME OF ARRIVAL UNCERTAINTY - Methods and a system for vehicle control are provided. The system includes an input device configured to receive a required time of arrival at a waypoint and a processor communicatively coupled to the input device. The processor is programmed to determine a forward late time profile, determine a forward early time profile representing the earliest time the vehicle could arrive at a point along the track and still arrive at the waypoint while transiting at a maximum available speed, and determine an estimated time uncertainty (ETU) associated with at least one of the forward late time profile and the forward early time profile. The system also includes an output device communicatively coupled to the processor, the output device configured to transmit the determined uncertainty with a respective one of the at least one of the forward late time profile and the forward early time profile to a display | 05-27-2010 |
20100131125 | METHOD FOR ASSISTING IN THE MANAGEMENT OF THE FLIGHT OF AN AIRCRAFT IN ORDER TO KEEP TO A TIME CONSTRAINT - The invention relates to the field of civil aviation and, more specifically, relates to the flight management systems, more commonly known by the English acronym FMS. The method for assisting in the management of the flight of an aircraft in order to keep to a time constraint according to the present invention allows for a control of the keeping to the time constraint that presents a rapid dynamic, by avoiding as far as possible having the estimated time of arrival (ETA) at a particular point (P) able to drift relative to a required time of arrival (RTA) at said particular point (P), thanks to the use of a manoeuvring margin (M) granted to the guidance module of the aircraft. | 05-27-2010 |
20100145552 | Route planning using ground threat prediction - Systems and methods are disclosed for determining an optimal flight path for an aircraft through a region of interest. A reroute region, which provides extreme boundaries for an optimal flight path, is defined around an initial flight path for the aircraft. A plurality of subregions are defined within the reroute region. Each of the plurality of subregions represent one of a plurality of representative times at which the airplane is expected to arrive at an associated location on the initial flight path. The position of at least one threat is predicted at each of the plurality of representative times. A cost is assigned to each cell in each subregion according to the predicted position of the at least one threat source at the representative time associated with the subregion. The optimal path is determined as a path through the reroute region having a lowest total cost. | 06-10-2010 |
20100145553 | METHOD AND DEVICE FOR SHARING DATA BETWEEN ON-BOARD SYSTEMS IN AN AIRCRAFT - The object of the invention is in particular a method and a device for exchanging data between a technical management system of an aircraft and a mission management system of the said aircraft, in order to permit one of the said systems to determine the consequences of an event detected in the other of the said systems. After at least one event has been detected ( | 06-10-2010 |
20100145554 | DEVICE AND METHOD FOR AUTOMATICALLY GENERATING A CONTROL ORDER FOR AN AIRCRAFT CONTROL SURFACE - A device and a method for automatically generating a control order of an aircraft control surface | 06-10-2010 |
20100145555 | Flight Control System - A system and method for a controlling an aircraft with flight control surfaces that are controlled both manually and by a computing device is disclosed. The present invention improves overall flight control operation by reducing the mechanical flight control surface components while providing sufficient back-up control capability in the event of either a mechanical or power-related failure. Through the present invention, natural feedback is provided to the operator from the mechanical flight control surface which operates independent of computer-aided flight control surfaces. Further, through the present invention, force input signals received from the pilot are filtered to improve the operation of the computer-aided flight control surfaces. | 06-10-2010 |
20100152923 | DYNAMIC DISPLAY OF NAVIGATIONAL INFORMATION - A display system for dynamically displaying aircraft flight information. The system includes a processor, memory, and a display. The processor is capable of communicating with the memory, the display, and a system environment of the aircraft. The processor is configured to display a flight map for the aircraft on the display, to evaluate state variable(s) dynamically representing state(s) in the aircraft system environment, and dynamically modify the flight map based at least in part on the evaluation. | 06-17-2010 |
20100152924 | NEXT GENERATION ELECTRONIC FLIGHT BAG - An electronic flight bag for an aircraft includes a display device and a processing system. The display device is operable to render various images. The processing system is in operable communication with the display. The processing system is configured to receive various types of data from various aircraft systems and is operable, upon receipt of the data, to supply display commands to the display device that cause the display device to automatically render various images. These images may include, among other things, flight manual pages, checklists, approach charts, maintenance data, and various navigation displays. The electronic flight bag may also implement the functions of various other aircraft systems and devices. | 06-17-2010 |
20100152925 | METHOD AND DEVICE FOR DETECTING OSCILLATORY FAILURES IN A POSITION SERVOCONTROL SUBSYSTEM OF AN AIRCRAFT CONTROL SURFACE - The detection device ( | 06-17-2010 |
20100152926 | DYNAMIC ADJUSTMENT OF WING SURFACES FOR VARIABLE CAMBER - The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity (CG), vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces. | 06-17-2010 |
20100152927 | METHOD AND DEVICE FOR OPTIMIZING THE FLIGHT OF AN AIRCRAFT - The invention relates to a method for optimizing the flight of an aircraft comprising a flight management system, the said flight management system using a first cost index (CI | 06-17-2010 |
20100152928 | SYSTEM FOR SECURING THE DISPLAY OF INSTRUCTIONS ORIGINATING FROM AIR TRAFFIC CONTROL - The system for automatically registering flight instructions for aircraft comprises a flight computer delivering a first set of flight instructions defining a pre established flight plan, called CONS_FMS, the system comprising a display, the display representing the current flight instructions, the system comprising a device for controlling instructions which comprises means of adjusting a second set of flight instructions, called CONS_PILOTE, the system comprising a manager of instructions originating from air traffic control, the instructions being transmitted by means of a data link, said instructions defining a third set of instructions, called CONS_CONTROLEUR. | 06-17-2010 |
20100161153 | METHOD AND APPARATUS FOR AUTOMATICALLY DETERMINING STOPOVER AIRPORTS FOR FLIGHT PLANNING - A method and apparatus that automatically selects one or more stopover airports (or “technical stops”) for flight planning is disclosed. The method may include receiving flight origin, destination, aircraft identification information, aircrew identification information, passenger identification information, and user preference information from a user, receiving weather, safety-of flight and meteorological information based on at least the received origin and destination information, retrieving aircraft information, origin and destination airport information, potential stopover airport information, aircrew information, and passenger information from one or more databases based on at least one of the received flight origin, destination, aircraft identification information, aircrew information, passenger information, and user preference information, automatically selecting one or more stopover airports based on the received weather, safety-of flight and meteorological information and the retrieved flight origin, destination, aircraft information, aircrew information, passenger information, and user preference information, and outputting the selected one or more stopover airports to the user. | 06-24-2010 |
20100161154 | OPERATIONS SUPPORT SYSTEMS AND METHODS WITH POWER MANAGEMENT - A power management system includes a data fusion unit configured to receive first health indicators from an engine diagnostics module and second health indicators from a power assurance module. The data fusion unit is configured to data fuse the first and second health indicators. A power assessment and decision support unit is coupled to the data fusion unit and configured to generate power available based on the fused first and second health indicators. A system diagnostic reasoner unit is coupled to the data fusion unit, and configured to provide a system level fault diagnosis based on the fused first and second health indicators. A graphical user interface is coupled to the power assessment and decision support unit and the system diagnostic reasoned unit. The graphical user interface is configured to display the system level fault diagnosis and the power available. | 06-24-2010 |
20100161155 | AUTOMATIC FLIGHT CONTROL HELICOPTER - The invention relates to an autonomous helicopter for recreational purposes or for a swarm-type surveillance system, characterised in that the helicopter has a complete automatic flight control, and in that the flight thereof is stable and automatic due to a device for the automatic control of the altitude, comprising at least two optical receivers, at least one optical emitter, at least two channels for processing signals of the receivers, and at least two motors controlling at least two propellers, at a speed proportional to the total amount of signals received. Said helicopter avoids obstacles by means of an orientation device controlled by the difference between the signals of the two receivers. It advances at a regular speed by means of a shift of the centre of gravity thereof in front of the axis of the two lifting propellers. | 06-24-2010 |
20100161156 | DEVICE FOR ASSISTING IN THE CHOICE OF A DIVERSION AIRPORT - The invention relates to a device for assisting in the choice of a diversion airport for an aircraft piloted by a crew ( | 06-24-2010 |
20100161157 | DEVICE FOR MANAGING PILOTING TASKS CARRIED OUT BY A CREW OF AN AIRCRAFT - The present invention lies in the field of embedded flight management systems on board aircraft. The invention relates notably to a system for managing alerts and procedures, and more precisely to a device for managing piloting tasks carried out by a crew of an aircraft. The device for managing tasks ( | 06-24-2010 |
20100168935 | METHOD OF AND SYSTEM FOR MAINTAINING OPERATING PERFORMANCE OF A TRANSPARENCY - Repair or replacement of a transparency mounted in body of a vehicle, e.g. an aircraft when one or more properties of the transparency is (are) operating outside of an acceptable limit(s) is arranged by monitoring operating performance of a property of the transparency, e.g. by mounted a sensor, e.g. a sensor for detecting moisture; a sensor for detecting impacts and vibrations; a sensor for detecting fractures; a sensor for detecting electric arcing, and a sensor for measuring temperature of an electrically conductive coating, on the transparency. Scheduling repair or replacement of the transparency at a geographical area when the operating performance of the property is outside an acceptable operating performance limit, and forwarding the schedule to the vehicle and to a maintenance location to prepare for the repair or replacement of the transparency at the geographical work area. | 07-01-2010 |
20100174423 | METHOD AND A SYSTEM FOR AUTOMATICALLY MANAGING CHECK LISTS ON AN AIRCRAFT - A method and a system for automatically managing check lists on an aircraft. | 07-08-2010 |
20100179710 | METHOD AND DEVICE FOR MANAGING, PROCESSING AND MONITORING PARAMETERS USED ON BOARD AIRCRAFT - A standardized identification code is used to identify each flight parameter used on board an aircraft and to provide some of its characteristic information. Descriptive complementary information is advantageously associated with the identification codes to form parameter identification maps stored, for example, in a shared database. The parameter identification codes may in particular be used to perform certain checks when parameter values are received. These checks make it possible to process only the monitored parameter values and to generate alerts if an inconsistency is detected. | 07-15-2010 |
20100185343 | METHOD OF CONTROLLING AN AIRCRAFT, THE METHOD IMPLEMENTING A VOTE SYSTEM - In the method of controlling an aircraft, a device implements the steps consisting in determining a first global value on the basis of only some amongst first individual values calculated by respective applications modifying at least one parameter to take account of how the determination step took place and determining a second global value on the basis of second individual values calculated by the respective applications and on the basis of the parameter(s). | 07-22-2010 |
20100198431 | MAINTENANCE COMPUTER SYSTEM FOR AN AIRCRAFT - A maintenance computer system for an aircraft, including a network partitioned into a secured avionics zone and an open zone. The system includes a first software module accommodated in the avionics zone and a second software module accommodated in the open zone, the first module configured to follow a fault-finding logic tree, and the second module configured to present an electronic maintenance document, with the path along the fault-finding logic tree followed by the first module automatically and synchronously generating a presentation by the second module of pages of the maintenance document associated respectively with nodes of the tree. | 08-05-2010 |
20100211236 | WIRELESS ENGINE MONITORING SYSTEM - A wireless engine monitoring system (WEMS) includes an engine monitoring module that is mounted directly on an aircraft engine and records, stores, encrypts and transmits full flight engine data. The system preferably interfaces to the Full Authority Digital Engine Controller/Engine Control Unit (FADEC/ECU) and can record hundreds of engine parameters with a preferred sampling frequency of about one second. The engine monitoring module is preferably formed as a miniaturized module directly mounted on the aircraft engine within its cowling and has a conformal antenna. The engine monitoring module can also upload data for onboard processing. | 08-19-2010 |
20100217458 | INTERACTIVE INFORMATION SYSTEM FOR AN AIRPLANE - An interactive information system is indicated for an aircraft to provide passengers with information, which access both an onboard data storage device and an off-board data storage device. A computer uses the onboard and off-board data to compute informative data, which are then visualized to the passenger. The passenger can interactively determine the form and type of data generation and preparation at any time. | 08-26-2010 |
20100217459 | Method for Aiding the Formulation of the Speed Strategy of an Aircraft with a View to Adhering to a Time Constraint - The invention relates to a method for formulating the strategy of an aircraft, with a view to favouring adherence to a time constraint. | 08-26-2010 |
20100222942 | TAXI BRAKE INHIBIT SYSTEM - A taxi brake inhibit system overcomes problems of discontinuities in pedal “feel” that can occur by use of a taxi brake inhibit system, by adding a new pedal “feel” logic in which twice the brake force is commanded for a given brake pedal application when taxi brake inhibit is active. The taxi brake inhibit system relies upon two different brake force vs. brake pedal application curves to compensate for the difference in deceleration that is achieved for a given brake pedal application depending upon whether the taxi brake inhibit is active or inactive. Such system effectively eliminates undesirable deceleration bumps, yaw effects and changes in pedal feel during braking. The taxi brake inhibit feature is also shut off to both fore-aft brake pairs if any non-normal taxi brake inhibit condition exists on either fore-aft brake pair. | 09-02-2010 |
20100228406 | UAV Flight Control Method And System - Disclosed herein is a method and system for flying a ducted-fan air-vehicle, such as an unmanned air-vehicle. The method includes receiving a first input associated with a target point of interest and pointing the gimbaled sensor at the target point of interest. The method further includes receiving a second input corresponding to a desired flight path and selecting a velocity vector flight command to achieve the desired flight path. Selecting the velocity vector flight command includes converting attitude data from the gimbaled sensor into a velocity vector flight command. The method further includes operating the flight of the UAV according to the selected velocity vector flight command and the gimbaled sensor remains fixed on the target point of interest during the flight of the UAV. | 09-09-2010 |
20100241291 | Autotiller control system for aircraft utilizing camera sensing - An automatic control system for directional control of an aircraft moving on the ground utilizing computer vision methods and camera sensing methods (visible, infrared or microwave) to optically recognize and track taxiway navigation features thereby providing pilot television picture steering cues or force inputs to the nosewheel steering system to maintain the aircraft on the centerline. | 09-23-2010 |
20100241292 | PREDICTED PATH SELECTION SYSTEM AND METHOD FOR HAZARD CODING IN SELECTIVELY CONSTRAINED AIRCRAFT CONTROL SYSTEMS - A surveillance system detects potential hazards and alerts the pilot to them. The alerts can be modified to indicate proximity to the predicted path of the aircraft. An autopilot receives instructions from a flight management system (FMS) regarding a planned path and is subject to constraints preempting the planned path. The surveillance system selects which of the planned and a constrained path will be followed for alerting and hazard coding purposes. Means are disclosed to determine when the constrained path will be followed by evaluating the current position of an aircraft, the planned path, and the constraint data. | 09-23-2010 |
20100250025 | METHODS AND SYSTEMS FOR REVIEWING DATALINK CLEARANCES - Provided are methods and systems for the automatic assessment and presentation of data on a display device that describes the operational impact on mission critical parameters resulting from a change in a vehicle's mission plan. The change in mission plan may be inputted manually by the vehicle operator but may also be received electronically and automatically over a data up link from an outside authority. | 09-30-2010 |
20100250026 | Interactive Navigation Device - The subject of the invention is an interactive navigation device comprising at least one navigation screen making it possible to display a graphical representation of at least one flight plan, a flight plan being composed of points and of segments. The device comprises means for displaying several flight plans simultaneously on the navigation screen at the same time as flight information text fields associated with the points of the said flight plans, the flight information fields being displayed in a manner contiguous with the points associated with them so as to be able to compare them conveniently. The device also comprises means for displaying on the navigation screen flight information fields associated with the segments of the flight plans, the said flight information fields being displayed in a manner contiguous with the segments associated with them. | 09-30-2010 |
20100250027 | METHOD TO REDUCE CARBON BRAKE WEAR THROUGH RESIDUAL BRAKE FORCE - The method for reducing aircraft carbon brake wear involves monitoring the commanded initiation of braking, and setting a residual brake clamping force to a predetermined minimum residual brake clamping force, which is maintained following the commanded initiation of braking to prevent release of braking during taxiing of the aircraft. The minimum residual brake clamping force is applied despite a commanded release of braking until at least one predetermined control logic condition occurs. | 09-30-2010 |
20100250028 | SYSTEM AND METHOD FOR AIRCRAFT BRAKING SYSTEM USAGE MONITORING - The system and method for monitoring wear of one or more aircraft parts, such as an aircraft brake, an aircraft tire, a standby system, and landing gear. One or more sensors are provided for sensing a parameter of usage, and an estimate of usage of the part can be determined based upon the signal indicating the sensed value of the parameter of usage of the aircraft part. A plurality of sensors can be provided for sensing usage of a plurality of parts of the aircraft, and the estimate of usage of the part can be stored for access of the estimate by ground personnel. As applied to monitoring wear of an aircraft brake, a linear brake wear indicator attached to the brake moves a discrete distance when the brake is actuated, and a linear position encoder measures the distance traveled by the linear brake wear indicator as an indication of brake usage. A wheel speed monitor may also be provided for measuring the aircraft wheel speed, for distinguishing between static brake applications and moving brake applications, based upon the wheel speed signal. | 09-30-2010 |
20100262318 | Electronic flight bag user interface system - An electronic flight bag user interface system that has a multi-function flight information display unit in electronic communication with a remote processing unit. The processing unit is in electronic communication with an aircraft avionics system. Pre-loaded flight information allows the user to access and display flight information on the display unit in digital electronic format, including charts and plates, flight manuals, weather information, camera viewing information, ship library information, and revision status of software programmed in the processing unit and revision status of pre-loaded charts, plates and manuals. The system operates on a single or a dual operating system platform, a Windows® based operating system and the other based on a DO178B certified operating system. | 10-14-2010 |
20100262319 | METHODS AND SYSTEMS FOR DISPLAYING ASSISTANCE MESSAGES TO AIRCRAFT OPERATORS - Methods and systems for displaying assistance messages to aircraft operators are disclosed. A method in accordance with one embodiment includes receiving an input from an aircraft operator at an aircraft flight deck, comparing a characteristic of the input to at least one target value for the characteristic, and, if the characteristic of the input differs from the at least one target value for the characteristic by at least a threshold amount, displaying an assistance message to the aircraft operator. The assistance message can include a complying input and/or an instruction for creating a complying input. The input and the assistance message can be displayed simultaneously. | 10-14-2010 |
20100268403 | VEHICLE MONITORING SYSTEM - An example reconfigurable vehicle monitoring arrangement includes a housing securable relative to a vehicle, a communication base at least partially disposed within the housing, and a universal connector assembly configured to selectively operatively connect the communication base with a plurality of different modules. At least one of the modules is configured to communicate data gathered from a plurality of vehicle data sources to the communication base. | 10-21-2010 |
20100268404 | METHOD AND SYSTEM TO INCREASE ELECTRIC BRAKE CLAMPING FORCE ACCURACY - The method and system for increasing accuracy of clamping force of electric aircraft carbon brakes, once braking has been commenced, provides a first pair of electric brake actuators with a range of low brake clamping force responsive to low brake clamping force commands, and a second pair of electric brake actuators with a range of high brake clamping force responsive to high brake clamping force commands. The first pair of electric brake actuators is actuated to apply a minimum residual braking force once wheel braking is commenced, and the second pair of electric brake actuators is actuated only when the commanded braking force is in the high range of brake clamping force. | 10-21-2010 |
20100274415 | TIME-TO-GO MISSILE GUIDANCE METHOD AND SYSTEM - A method and apparatus for guiding a vehicle to intercept a target is described. The method iteratively estimates a time-to-go until target intercept and modifies an acceleration command based upon the revised time-to-go estimate. The time-to-go estimate depends upon the position, the velocity, and the actual or real time acceleration of both the vehicle and the target. By more accurately estimating the time-to-go, the method is especially useful for applications employing a warhead designed to detonate in close proximity to the target. The method may also be used in vehicle accident avoidance and vehicle guidance applications. | 10-28-2010 |
20100274416 | DISTRIBUTED APPROACH TO ELECTRONIC ENGINE CONTROL FOR GAS TURBINE ENGINES - A distributed electronic engine control system includes an airframe module, an electronic engine control module, and an engine I/O module. The modules are arranged in locations remote from one another. A serial communications bus interconnects the modules with one another. A first engine controls device is connected to the engine I/O module and is configured to interact with an engine component and provide a first data. The engine I/O module includes inner loop control logic that uses the first data and produces a second data in response thereto. The electronic engine control module includes an outer loop control logic using the second data and produces a third data in response thereto. The airframe module receives power and distributes the power to the electronic engine control and engine I/O modules. The first, second and third data are provided on the serial communications bus. | 10-28-2010 |
20100274417 | System and Method of Interaction and Holistic Representation of Tasks - The general field of the invention is that of viewing systems comprising first means making it possible to process and to store the various data necessary for the accomplishment of a technical or industrial process, second means making it possible to determine the various tasks to be accomplished by a user in the course of the process on the basis of the previous data, a computer for generating graphical images associated with a viewing device and a man-machine interface with the said viewing device. The viewing device according to the invention displays a succession of graphical icons, each icon representing a task to be accomplished, the various icons being ordered according to a time scale extending from the start to the end of the process. The system and the method according to the invention are of global or holistic types. A certain number of operations on these icons can be performed by means of the man-machine interface. The favoured field of the invention is that of aircraft instrument panels. | 10-28-2010 |
20100274418 | Method for Determining the Quantity of Fuel Taken On Board an Aircraft Making it Possible to Maintain a Time Requirement of the RTA Type - A method for determining the quantity of fuel in an aircraft and an optimization criterion such as a cost index, notably used in an FMS, making it possible to maintain a time requirement of the RTA type, comprising a first step of computing the optimization criterion CI | 10-28-2010 |
20100280682 | METHOD FOR ACTIVE POWER MANAGEMENT AND ALLOCATION OF FUNCTIONALITY - Methods for active power management, i.e., the power management method may be activated in response to changes in the supply and demand of power in a system, are disclosed. The power management method may use dynamically collected data reporting levels of electrical power utilized by systems while matching them to the available power. One embodiment of the present invention may be applied in smaller or medium sized systems. Another embodiment of the present invention may be implemented making use of additional aircraft resources, such as an integrated modular avionics (IMA) line replaceable unit (LRU) in larger sized systems. Both of these embodiments may make use of data collected from systems utilizing or generating electrical via the bus power control unit (BPCU) LRU, the data processing taking place either locally in the BPCU (small or medium sized systems) or in the IMA (larger systems). | 11-04-2010 |
20100286848 | INTEGRATING AVIONICS FUNCTIONS - Systems, methods and computer program products for integrating one or more avionics functions are provided herein. In an embodiment avionics functions (e.g., ADS-B functions) are integrated by (1) receiving input from at least one avionics function module that executes at least one avionics function; (2) determining which of the avionics functions to allow to be engaged simultaneously, based on at different factors. In addition, embodiments select from different algorithms for the connected avionics functions. | 11-11-2010 |
20100292869 | AIRCRAFT DISPATCH INFORMATION - Systems and methods to manage aircraft dispatch information are provided. A particular method includes receiving fault information at a dispatch information computing system. The fault information is associated with an aircraft. The method also includes accessing operational restriction information associated with the aircraft based on the fault information. The method further includes automatically determining a set of bottom line operational limitations of the aircraft based on the fault information and the operational restriction information. The method also includes generating customized checklists for the various users of the information. The method also includes sending output data from the dispatch information computing system to an output device. The output data identifies the set of bottom line operational limitations of the aircraft and tasks to be completed by the various users. | 11-18-2010 |
20100292870 | FADEC AND AVIONIC COMPONENT DISTRIBUTED ARCHITECTURE - The invention relates to a device for motorized aircraft comprising at least one avionic component ( | 11-18-2010 |
20100292871 | ADAPTIVE SURVEILLANCE AND GUIDANCE SYSTEM FOR VEHICLE COLLISION AVOIDANCE AND INTERCEPTION - A surveillance and guidance method and system for use with autonomously guided, man-on-the-loop or man-in-the-loop guided vehicles where the presence of obstacles must be considered in guiding the vehicle towards a target includes a navigation system configured to determine the position of the vehicle on which it is equipped. A communication system is configured for data exchange between the vehicle, neighboring vehicles and ground stations. A surveillance system is configured to detect and locate fixed or moving targets and obstacles. A computer is configured to track the position of targets and obstacles and to provide guidance commands or 4D flight paths to perform collision avoidance with respect to traffic regulations and procedures, and operational airspace restrictions. Additional computer tasks include station keeping or interception of targets. A command and control system is configured to interact with a user interface and control the vehicle's actuators. | 11-18-2010 |
20100305780 | FLIGHT CONTROL SYSTEM AND METHOD OF SEPARATING CONTROL LEVER LINKAGE - A flight control system according to the present invention includes a first sensor, a flight control computer, a link mechanism, a separation unit, and a second sensor detecting a force transmitted from the first control lever to the link mechanism. The first sensor detects a force applied from an outside to a first control lever. The flight control computer determines whether or not stacking arises in the first control lever on the basis of the force detected by the first sensor and the force detected by the second sensor, and outputs a separation command to the separation unit when determining that the stacking arises. The separation unit disconnects the link mechanism on the basis of the separation command to separate a connection between the first control lever and the second control lever. | 12-02-2010 |
20100305781 | PREDICTING AIRCRAFT TRAJECTORY - The present invention provides a computer-implemented method of producing a description of aircraft intent expressed using a formal language. The description may be used to predict aircraft trajectory, for example by air traffic management. Rules are used in association with information provided to generate a set of instructions describing both the aerodynamic configuration of the aircraft and the motion of the aircraft. These instructions are checked to ensure that they describe unambiguously the aircraft's trajectory. The instructions are then expressed using a formal language. | 12-02-2010 |
20100305782 | AIRBORNE RIGHT OF WAY AUTONOMOUS IMAGER - An automated airborne video recording system for imaging pipeline or electric line rights-of-way, irrigation canals, or any other linear ground features. The system includes a gimbaled, stabilized camera system, a data recorder, and autonomous imager software that computes the shortest vector between the aircraft position and the pipeline based on the aircraft GPS and the Geographic Information Database. The system then commands the stabilized camera system to point directly at the pipeline regardless of the aircraft position and orientation, automatically collecting continuous NTSC or digital video of the entire right of way. | 12-02-2010 |
20100318243 | Method and Apparatus for Wireless Aircraft Communications and Power System Using Fuselage Stringers - A method and apparatus for transmitting wireless signals. An apparatus comprises a stringer having a channel and a waveguide located within the channel. The waveguide is capable of carrying a number of wireless signals. | 12-16-2010 |
20100318244 | Implementing Continuous Descent Approaches for Maximum Predictability in Aircraft - The present disclosure relates to methods of calculating and flying continuous descent approaches to an airport or the like, and to aircraft navigation systems for implementing these methods. The present disclosure resides in the recognition that greater predictability in arrival times may be achieved by flying continuous descent approaches by maintaining a constant aerodynamic flight path angle. | 12-16-2010 |
20100318245 | FLIGHT CONTROL SYSTEM - A flight control system for an aircraft includes a PCS generating a pilot control signal based on pilot operations of a stick control and others, an FCC for controlling flight control surfaces of the aircraft, a surface control device arranged for each flight control surface to control it based on a surface control signal transmitted from the FCC, and a data bus for connecting the FCC and the surface control device. The surface control device includes an ACE executing servo calculation process and outputting an actuator operation signal, and an actuator section for controlling hydraulic oil supplied to a hydraulic cylinder based on the actuator operation signal. A single flight control surface is controlled by a plurality of ACE and actuator section pairs, and the ACE includes a normal control section, a monitoring section, a backup control section, and the like. | 12-16-2010 |
20100324754 | Samara wing - A samara wing including a main wing with a leading edge and a trailing edge. An aileron has a leading edge and a trailing edge and is pivotally attached proximate the trailing edge of the main wing and separated therefrom by a gap. The aileron is rotatable between the first position where the trailing edge of the aileron is facing forward in a plummet mode of operation and a second position where the trailing edge of the aileron is facing rearward typically for an autorotation mode of operation. | 12-23-2010 |
20100324755 | Method and system for resolving traffic conflicts in take-off and landing - A method and system for resolving existing and potential traffic conflicts that may occur during take-off and landing in aviation that includes means of monitoring movements on the runway, its approaches and environs to determine whether a conflict or potential conflict exists, means to resolve a conflict and to generate an output pertaining to this resolution. | 12-23-2010 |
20100324756 | SYSTEMS AND METHODS FOR VALIDATING PREDETERMINED EVENTS IN RECONFIGURABLE CONTROL SYSTEMS - Systems and methods for validating predetermined events in reconfigurable control systems are provided. One method includes receiving, by a plurality of redundant processors operating in a first mode, a notice from two of three redundant sensors that the predetermined event occurred and reconfiguring the plurality of redundant processors to operate in a second mode in response to the notice. Another method includes receiving a first notice that one or more sensors detected that a first vehicle is coupled to a second vehicle at a primary control system and a secondary control system and reconfiguring the primary control system and the secondary control system to operate in another mode at substantially the same time in response to the notice. | 12-23-2010 |
20100324757 | Method and Device for Optimizing the Deceleration Point of a Holding Circuit - A method for optimizing the computation of the position of the braking point on the approach to a holding circuit for aircraft is provided. The method comprises computing the optimal position of the theoretical deceleration point allowing the aircraft to pass from its current speed to the maximum speed authorized at the entry point and of the theoretical deceleration distance, computing a trajectory portion forming a turn allowing the aircraft to enter the holding circuit and the position of the point of the start of the turn, computing a point for anticipating the turn, making it possible to take into account the banking rate of the aircraft, computing a margin, and computing the start-of-braking point, situated at a distance. | 12-23-2010 |
20100324758 | Compound Aircraft Control System and Method - The Invention is a control system for a compound aircraft. A compound aircraft has features of both a helicopter and a fixed wing aircraft and provides redundant control options. The control system allows an authorized person to select any of plurality of operational objectives each of which is designed to achieve any particular command. | 12-23-2010 |
20100332052 | FAULT TOLERANT FLIGHT CONTROL SYSTEM - A method, apparatus, and computer program product for identifying a number of air states for a vehicle. A deflection of a control surface associated with an actuator is identified to form an identified deflection. A current in the actuator is identified to form a measured current. The number of air states for the vehicle is estimated using the identified deflection and the measured current. | 12-30-2010 |
20100332053 | METHODS AND SYSTEMS FOR FAULT DETERMINATION FOR AIRCRAFT - A method for fault determination for an aircraft includes the steps of generating a predicted maneuver of the aircraft using an aircraft operating input and a model of aircraft performance, determining an actual maneuver of the aircraft using information obtained from an inertial measurement system, comparing the predicted maneuver and the actual maneuver, and determining a fault of the aircraft based on the comparison of the predicted maneuver and the actual maneuver. | 12-30-2010 |
20100332054 | AUTOMATED DECISION AID TOOL FOR PROMPTING A PILOT TO REQUEST A FLIGHT LEVEL CHANGE - Provided are methods and systems for the automatic calculation and presentation of data on a display device alerting a pilot that a change in flight plan is desirable, possible and administratively compliant under air traffic control protocol. The methods and systems may automatically request the flight clearance over a data link or the pilot may override the data link. | 12-30-2010 |
20100332055 | ASSISTANCE PROCESS AND DEVICE FOR MANAGING AN IN-FLIGHT REFUELING - An assisting process and device for managing an in-flight refueling is disclosed. The device ( | 12-30-2010 |
20110004361 | METHOD AND DEVICE FOR ESTIMATING THE FORCES EXERTED ON A CONTROL SURFACE OF AN AIRCRAFT - The device ( | 01-06-2011 |
20110010026 | Calibration Method for Aerial Vehicles - Aerial vehicles make good remote sensing platforms by reducing the cost and making imagery easier to obtain. The low altitude, small image footprint and high number of images make it difficult and tedious to georeference the images based on features. Auto-orthorectification techniques based on the position and attitude of the aerial vehicle would work well except the inherent errors in the aerial vehicle sensors reduce the accuracy of the orthorectification significantly. The orthorectification accuracy is improved by calibrating the aerial vehicle sensors. This is done by inverse orthorectifing the images to find the actual position and attitude of the aerial vehicle using ground references setup in a square. | 01-13-2011 |
20110022249 | Distributed Architecture for All Radionavigation Aids - The present invention relates to a distributed architecture for all aerial navigation aids. So that this architecture makes it possible to reduce the weight and/or the bulk of the cables linking the antennas to the corresponding equipment, as well as the weight and/or the bulk of at least part of said equipment, a part at least of the receivers is sited remotely in proximity to the corresponding antennas, and a part at least of the power supply for the equipment of the aircraft is centralized, and this centralized supply distributes a stabilized DC power supply to the remotely sited equipment. | 01-27-2011 |
20110029158 | METHOD AND SYSTEM FOR VERTICAL NAVIGATION USING TIME-OF-ARRIVAL CONTROL - A method and systems for controlling a speed of a vehicle are provided. The control system includes an input device configured to receive a required time of arrival (RTA) at a waypoint and a processor communicatively coupled to said input device, said processor programmed to automatically determine a dynamically adjustable range for an autothrottle control using an RTA error and a speed control tolerance, the RTA error representing a difference between an estimated time of arrival (ETA) and the RTA, the speed control tolerance representing a tolerance range about the vehicle speed profile. The control system also includes an output device communicatively coupled to said processor, said output device is configured to transmit at least one of a thrust control signal and a drag control signal to a speed control system of the vehicle. | 02-03-2011 |
20110029159 | METHOD AND DEVICE FOR REDUCING ON AN AIRCRAFT LATERAL EFFECTS OF A TURBULENCE - A method and device for reducing on an aircraft lateral effects of a turbulence. The device ( | 02-03-2011 |
20110040428 | TRANSPORTATION INFORMATION MANAGEMENT SYSTEM - A computer-implemented transportation information management system and method permits entry, recording, and transmission of operation and maintenance data related to FAA recordkeeping and recording requirements within an SQL database. A secure website permits entry and display of operation and maintenance data as well as facilitating data input using input devices such as a cellular telephone, a personal digital assistant, a personal computer, and a portable computer. The system outputs aircraft operation and maintenance data, automatic alerts of pilot flight and duty time limitations, and flight tracking and monitoring information via a spreadsheet, electronic mail message, text message, and a completed FAA mandatory reporting requirement forms to the aforementioned data input devices. Operation and maintenance data is automatically and continuously transferred to the FAA to populate FAA flight tracking data systems and air traffic control data system. | 02-17-2011 |
20110040429 | ACTIVE VIBRATION DAMPING (AVD) SYSTEM FOR PRECISION POINTING SPACECRAFT - An active vibration damping (AVD) control system for spacecraft provides a simple-to-implement and robust formulation that provides a novel damping control method for reducing spacecraft structural vibrations and improving antenna and instrument pointing. The AVD control system comprises an excitation signal generator configured to generate excitation input signals, and a damping model identification unit configured to receive system identification data and configured to produce control model parameters, the system identification data comprising the excitation input signals and information associated with motion of the spacecraft. The AVD control system further comprises an AVD control unit configured to receive the control model parameters, the AVD control unit configured to produce AVD control signals to control one or more actuators of the spacecraft. | 02-17-2011 |
20110040430 | INTEGRITY MONITORING OF INERTIAL REFERENCE UNIT - Systems, methods, and machine-executable programming products adapted for the control of aircraft or other vehicles by receiving from at least one Inertial Reference System (IRS), including a plurality of Inertial Reference Units (IRUs), signals representing vehicle state data; receiving from at least one Augmented Direct Mode Sensor (ADMS) signals representing independently-acquired vehicle state data corresponding to at least a subset of the signals received from the IRS; performing signal selection and fault detection processes on the signals received from the at least one IRS and on the corresponding signals received from the ADMS; based at least partly on the signal and fault detection processes, determining whether at least one component of at least one of the IRS and ADMS is in a fault condition; and based on the fault condition, providing to at least one vehicle control system device one or more vehicle control command signals. | 02-17-2011 |
20110046817 | Incremental Position-Based Guidance For A UAV - Disclosed herein is a method and system for flying a ducted-fan aerial vehicle, such as an unmanned aerial vehicle (UAV). The method includes receiving a flight plan comprising a plurality of waypoints and a plurality of path segments connecting the plurality of waypoints in an order of execution. The method further includes determining actual flight instructions for the ducted fan unmanned aerial vehicle based on (i) the received flight plan, (ii) a predetermined set of operating parameters associated with the ducted fan unmanned aerial vehicle, and (iii) an iterative analysis of a plurality of ordered triples. The method further includes sending the actual flight instructions to at least one processor of the ducted fan unmanned aerial vehicle configured to implement one or more portions of the actual flight instructions. | 02-24-2011 |
20110046818 | ONBOARD AIRPLANE COMMUNITY NOISE AND EMISSIONS MONITOR - A method for monitoring airplane noise and emissions may include receiving a predetermined set of engine performance data for an airplane and receiving a predetermined set of airplane flight data for the airplane. The method may also include predicting at least one of a noise level and an emissions level from the airplane at each of a plurality of ground based noise and emissions monitoring stations based on the predetermined set of engine performance data and the predetermined set of airplane flight data. Each of the plurality of ground based noise and emissions monitoring stations is located at a predetermined geographic location along an expected flight path of the airplane. The method may also include presenting at least one of the predicted noise level and the predicted emissions level on a display to a pilot of the airplane to permit operation of the airplane to substantially minimize at least one of an actual noise level and an actual emissions level at each of the plurality of ground based noise and emissions monitoring stations. | 02-24-2011 |
20110046819 | METHOD AND SYSTEM FOR DEACTIVATING A STEERING SYSTEM OF AN AIRCRAFT'S FRONT LANDING GEAR - A method for deactivating a steering system of a front landing gear of an aircraft, including detecting an activated status of the steering system, detecting a pilot control unit in neutral position, detecting towing conditions of the aircraft, detecting a rotational movement of the nose gear, and deactivating the steering system when operations to are verified. The disclosed embodiments also concern a system for implementing this method. | 02-24-2011 |
20110046820 | TEST EQUIPMENT FOR TESTING AN ADDITIONAL CENTER TANK (ACT) SYSTEM OF AN AIRCRAFT - The present invention provides test equipment for testing an additional center tank (ACT) system of an aircraft. The ACT system comprising control means configured to perform functions of an Auxiliary Fuel Management Computer (AFMC) and an Auxiliary Level Sensing Control Unit (ALSCU). The test equipment comprises at least one test module adapted for coupling to the ACT system in place of at least a portion of the control means, the test module comprising means for generating one or more test signals and outputting the test signals to the ACT system. | 02-24-2011 |
20110046821 | Reconfigurable aircraft - A reconfigurable aircraft having a fuselage and a series of wing segments that form a wing, and an extra wing segment that is interchangeable with a wing segment that is part of the wing. The wing segments are readily attachable and detachable from the fuselage, allowing for the interchanging of the wing segments. At least one of the two interchangeable wing segments is configured with one type of mission-specific equipment, and the other may be configured with a second type of mission-specific equipment, allowing for the quick reconfiguration of the aircraft. Alternatively, the two interchangeable wing segments are each configured with the same mission-specific equipment, allowing for mission-specific equipment is serviced without interfering with the flight schedule. With an additional fuselage and set of wing segments that form a wing a mission may be continuously flown. | 02-24-2011 |
20110046822 | Method for Reducing Outside Air Inflow Required for Aircraft Cabin Air Quality - A method for calculating an aircraft fuselage leakage calculation of an aircraft is provided. The method comprises determining a calculation period for an aircraft fuselage leakage value and inputting the calculation period into a computer to obtain a first input data. The method further comprises obtaining one or more outside air inflow rates and inputting the one or more outside air inflow rates into the computer to obtain a second input data. The method further comprises obtaining one or more air outflow rates and inputting the one or more air outflow rates into the computer to obtain a third input data. The method further comprises accumulating the first input data, the second input data, and the third input data in the computer to obtain an accumulated input data. The method further comprises processing the accumulated input data with a process software to obtain an output data in the form of a calculated aircraft fuselage leakage value. The method further comprises sending the output data to a data file. The method further comprises using the calculated aircraft fuselage leakage value to calculate an aircraft fuel savings potential value. | 02-24-2011 |
20110054718 | DYNAMIC WEATHER SELECTION - The different advantageous embodiments provide a system comprising a weather band selection process and a processor unit. The processor unit is configured to run the weather band selection process. The weather band selection process identifies a flight trajectory associated with an aircraft, identifies weather information for the flight trajectory, and identifies a weather band selection for the aircraft using the flight trajectory, aircraft information and the weather information. | 03-03-2011 |
20110060482 | CONTROL ASSEMBLY - A control assembly operable in the event of overheating of an engine electronic controller on an aircraft. The assembly including one or more temperature sensors located in the vicinity of the aircraft engine and connected to a control unit. The control unit is arranged to measure the temperature or temperatures detected by the sensors, and to determine whether in view of detected increased temperatures, a situation constitutes an emergency situation or a controlled situation. The control unit communicates a controlled situation to a pilot of the aircraft, and automatically causes an override action to occur to the aircraft engine when an emergency situation is determined. | 03-10-2011 |
20110060483 | DEVICE FOR AIDING THE NAVIGATION AND GUIDANCE OF AN AIRCRAFT, AND SYSTEM COMPRISING SUCH A DEVICE - Device for aiding the navigation and guidance of an aircraft, and system comprising such a device. The device ( | 03-10-2011 |
20110066305 | MULTI-AXIS SERIALLY REDUNDANT, SINGLE CHANNEL, MULTI-PATH FLY-BY-WIRE FLIGHT CONTROL SYSTEM - A multi-axis serially redundant, single channel, multi-path fly-by-wire control system comprising: serially redundant flight control computers in a single channel where only one “primary” flight control computer is active and controlling at any given time; a matrix of parallel flight control surface controllers including stabilizer motor control units (SMCU) and actuator electronics control modules (AECM) define multiple control paths within the single channel, each implemented with dissimilar hardware and which each control the movement of a distributed set of flight control surfaces on the aircraft in response to flight control surface commands of the primary flight control computer; and a set of (pilot and co-pilot) controls and aircraft surface/reference/navigation sensors and systems which provide input to a primary flight control computer and are used to generate the flight control surface commands to control the aircraft in flight in accordance with the control law algorithms implemented in the flight control computers. | 03-17-2011 |
20110071705 | Aircraft Power Management - An electric power management system of a vehicle may interconnect a power plant, a propeller drive unit, and a battery via a bus. A controller may direct the operation of the power plant and the propeller drive unit. In a slow control mode, the propeller drive unit may react slowly to small throttle change requests. In the slow control mode, the propeller drive unit may draw power completely or substantially from the power plant. Upon a throttle request to rapidly change propeller drive unit speed more than a threshold amount, the controller may direct that the propeller drive unit quickly obtain the requested speed by drawing power required from the battery in excess of that being generated from the power plant. Subsequently, the controller may direct that the power plant increase power generation to maintain the propeller drive unit at the new speed, and recharge or float the battery. | 03-24-2011 |
20110071706 | METHOD FOR MANAGING POWER AND ENERGY IN A FUEL CELL POWERED AERIAL VEHICLE BASED ON SECONDARY OPERATION PRIORITY - A method for managing power flow within an aerial vehicle includes determining a fuel cell power limit and a battery energy reserve. The method further includes determining a flight operation power requirement. The method further includes determining priority levels of secondary operations and providing power for secondary operations based on the priority levels. | 03-24-2011 |
20110071707 | Method for Managing Power Boost in a Fuel Cell Powered Aerial Vehicle - An aerial vehicle is configured to operate in a base fuel cell operating mode and a fuel cell boost operating mode. A method for controlling the aerial includes providing a base fuel cell upper power limit. The method further includes controlling the fuel cell power level below the base fuel cell upper power limit when the aerial vehicle is operating in the base fuel cell operating mode. The method further includes operating the fuel cell above the base upper fuel cell power limit when the aerial vehicle is operating in the fuel cell boost operating mode. | 03-24-2011 |
20110071708 | ASSISTED PILOTING METHOD AND DEVICE FOR AN AIRCRAFT FOR USE IN THE EVENT OF A FIRST LIMIT INDICATOR BREAKING DOWN - An assisted piloting method for an aircraft having at least two engines ( | 03-24-2011 |
20110071709 | HIGHLY REPRESENTATIVE REAL-TIME SIMULATION OF AN AVIONICS SYSTEM - Optionally-mixed highly representative real time simulation of at least part of an avionics system ( | 03-24-2011 |
20110093140 | DEVICE FOR DETERMINING THE POSITION OF A THROTTLE LEVER IN AN AIRCRAFT - A device for determining a position of a throttle lever includes position sensors each connected to a primary flight control computer, position sensors each connected to an engine management computer, the position sensors being split into at least three groups of sensors with no common simple failure mode, and at least one interface computer, that includes at least one input to receive measurement information emitted by the computers connected to the position sensors and outputs leading to the engine management computer. | 04-21-2011 |
20110106342 | Absolute angle correction apparatus - The instant invention provides an absolute angle correction apparatus for correcting flight angle and direction of a wireless aircraft. The absolute angle correction apparatus includes a controlling signal module, a microcontroller, a transducer module, an output module, and a power module for supplying power. The controlling signal module receives wireless signals from a remote controller, decoding the received wireless signals, and transferring to the microcontroller as original input values. The transducer module measures acceleration and attitude of the aircraft, and transfers measured values to the microcontroller as variation parameters. The microcontroller receives the original input values and the variation parameters, together calculates and outputs precisely computed results. The output module controls flight steering of the aircraft according to the computed result from the microcontroller. The absolute angle correction apparatus corrects flight angle and direction of the aircraft timely and accurately. | 05-05-2011 |
20110112705 | ELECTRONIC CONTROL DEVICE FOR A PILOTING MEMBER WITH MULTIFUNCTIONAL MICROCONTROLLERS, PILOTING DEVICE AND AIRCRAFT - An electronic control device for an aircraft piloting member mounted on an electromechanical supporting box ( | 05-12-2011 |
20110118904 | METHOD AND SYSTEM TO REDUCE IMPACT OF NON-ATC DATALINK MESSAGES ON ATC DATALINK MESSAGES ON A SHARED AIR-GROUND COMMUNICATION LINK - A system to send air traffic control (ATC) data-link messages from an aircraft is provided. The system includes ATC applications in a first portion of an application layer, non-ATC applications in a second portion of the application layer; and a communication manager in the aircraft having two addresses for the aircraft. The communication manager includes a first copy of software in a first data link layer and a second copy of the software in a second data link layer. ATC data-link messages are sent from the aircraft independent of non-ATC data-link messages sent from the aircraft. | 05-19-2011 |
20110118905 | METHODS SYSTEMS AND APPARATUS FOR ANALYZING COMPLEX SYSTEMS VIA PROGNOSTIC REASONING - Methods and apparatus are provided for analyzing a complex system that includes a number of subsystems. Each subsystem comprises at least one sensor designed to generate sensor data. Sensor data from at least one of the sensors is processed to generate binary evidence of a sensed event, and complex evidence of a sensed event. The complex evidence has more sophisticated mathematical properties than the binary evidence. The complex evidence comprises one or more of: a condition indicator (CI), a health indicator (HI), and a prognostic indicator (PI). A system fault model (SFM) is provided that defines statistical relationships between binary evidence, complex evidence, and an underlying failure mode (FM) that is occurring in the complex system. The binary evidence and the complex evidence are processed to identify failure modes taking place within one or more of the subsystems. Based on the binary evidence and the complex evidence and the SFM, diagnostic conclusions can be generated regarding adverse events that are taking place within the complex system, and prognostic conclusions can be generated regarding adverse events that are predicted to take place within the complex system. | 05-19-2011 |
20110118906 | DISTRIBUTED FLIGHT CONTROL SYSTEM - A flight control system for an aircraft, controlling a plurality of actuators adapted to actuate control surfaces of the aircraft, including: at least one communications bus; at least one computer situated in the avionics bay of the aircraft, and adapted to calculate flight commands and to transmit them over the bus in the form of command messages; and at least a first remote terminal connected to the bus, adapted to control a control surface actuator, and to acquire the state of the actuator from information provided by at least a first sensor, the first terminal receiving command messages from the computer and transmitting electrical orders to the actuator as a function of the command messages received in this way, and also transmitting messages to the computer, at its request, relating to the state of the actuator as a function of the information provided by the first sensor. | 05-19-2011 |
20110118907 | MULTIPURPOSE MODULAR AIRSHIP SYSTEMS AND METHODS - Embodiments according to the methods and systems provide for the selection, assembly, deployment, exploitation of data collected, redeployment, retrieval and stowage of a remotely operated lighter than air (LTA) network of vehicles. From modular components stowed with a mobile platform, one or more LTA vehicles can be assembled, deployed and retrieved. Determining the desirable number of LTA vehicles and the modular components to be assembled for each vehicle can be performed through a computer recommending modular components based on mission parameters. A remote controller device can be used for pre-deployment setup, in-flight mission management and analysis of data gathered by a plurality of possible sensing devise operably attached to the one or more LTA vehicles. | 05-19-2011 |
20110125346 | PROTECTION ENVELOPE SWITCHING - An apparatus defines a protection envelope in an aircraft, including a processor and at least one sensor, each sensor being coupled with the processor, the processor executing at least one neural network based algorithm. The at least one sensor monitors flight parameters of the aircraft thereby generating monitored flight parameters. The processor divides the performance envelope of the aircraft into predefined flight regimes, wherein for each predefined flight regime, the processor defines and stores a suitable protection envelope. The processor determines an estimated flight regime of the aircraft using the neural network based algorithm based on the monitored flight parameters. The processor selects a respective suitable protection envelope for the aircraft based on the estimated flight regime. | 05-26-2011 |
20110137492 | STABILIZED APPROACH TO A POINT IN DEGRADED VISUAL ENVIRONMENT - A flight control system includes a fly by wire system operable to provide predictive termination point symbology overlaid on a synthetic imagery displayed by a display system in response to a control system and a sensor system. A method to facilitate a VTOL aircraft approach to a terminal point includes integrating a flight director mode with a control system to provide a stabilized approach path to a termination point. | 06-09-2011 |
20110137493 | Method for Continuously and Adaptively Generating a Speed Setpoint for an Aircraft to Observe an RTA - Method for generating a flight speed profile of an aircraft ( | 06-09-2011 |
20110137494 | Systems and Methods for Velocity Profile Based Approach to Point Control - A method for velocity profile based approach to point control for an aircraft includes determining a distance from the aircraft to a target point; determining a velocity command based on the distance to the target point and a desired acceleration; and issuing the velocity command. A velocity profile based approach to point control module for an aircraft and a computer program product comprising a computer readable storage medium containing computer code that, when executed by a computer, implements a method for velocity profile based approach to point control are also provided. | 06-09-2011 |
20110137495 | Method for Assisting in Rejoining a Vertical Descent Trajectory and Associated Device - A method is provided for assisting in rejoining a vertical descent trajectory that an aircraft is assumed to have to follow, using a flight management system FMS embedded onboard the aircraft, and includes the following steps: calculation of a vertical deviation VDEV, in the vertical plane, between the aircraft and the vertical descent trajectory, and comparison between the vertical deviation VDEV and a predetermined deviation threshold SVDEV; when the vertical deviation VDEV reaches the deviation threshold SVDEV, a step during which the activation of an optimized mode for catching up on the vertical descent trajectory is authorized; if the optimized mode for catching up on the vertical descent trajectory is activated, piloting of the aircraft by the flight management system FMS in optimized catch-up mode, that is to say at minimum thrust with a target rejoining speed in level VCRP and a target rejoining speed in downward trajectory, the target rejoining speed in level VCRP being equal to the maximum L/D ratio speed of the aircraft uprated by a first value V | 06-09-2011 |
20110137496 | METHOD AND APPARATUS FOR AUTOMATICALLY CONTROLLING AIRCRAFT FLIGHT CONTROL TRIM SYSTEMS - An automatic trim system and method is disclosed for automatically trimming a flight control surface of an aircraft. A force sensor measures a force applied by a pilot to a flight control system actuator. The length of time that the force is applied by the pilot is then timed by a tinier. A trim system to reduce the applied force is included on the flight control surfaces. A processor determines if trim is required if a predetermined amount of time is exceeded based on the force sensor measurement. The processor can set the trim system to the trim required therein. An airspeed sensor is used to verify that the aircraft has sufficient speed for flight. A force sensor can be utilized to measure the input force being applied by the pilot. If a pilot input force is applied to the controls and the aircraft is in a steady state, a timer can be activated. If the force sensor continues to sense a force after the tinier times for a predetermined time, the trim can he adjusted in the appropriate direction until the force sensor measures no significant pilot input force. | 06-09-2011 |
20110137497 | AIRCRAFT PROVIDED WITH A DEVICE FOR ASSISTING THE PILOT WHEN CARRYING AN EXTERNAL LOAD WITH A SLING, AND A METHOD IMPLEMENTED BY SAID DEVICE - The present invention relates to an aircraft ( | 06-09-2011 |
20110144832 | MULTIPLE TRANSITION RNP APPROACH PROCEDURE - A required navigation performance (RNP) approach method is described that includes providing a plurality of fixed, predetermined waypoints associated with at least one runway of at least one airport, providing a predetermined plurality of constant radius turnpoints connecting a downwind leg of the runway to a final approach leg of the runway, and assigning one of the constant radius turnpoints to an aircraft capable of flying an RNP approach, the turnpoint selected to provide separation from other approaching aircraft and a landing time for the aircraft. | 06-16-2011 |
20110144833 | SYSTEMS AND METHODS FOR PROVIDING AN IN-TRAIL PROCEDURE SPEED DIRECTOR - Embodiments of the present invention enhance existing ITP algorithms by providing additional information to the flight crew. The additional information may enable the flight crew to appropriately modify own aircraft airspeed, and thereby, ground speed, in order to qualify for ITP procedures. | 06-16-2011 |
20110144834 | MODULAR ARTICULATED-WING AIRCRAFT - Systems and/or methods for forming a multiple-articulated flying system (skybase) having a high aspect ratio wing platform, operable to loiter over an area of interest at a high altitude are provided. In certain exemplary embodiments, autonomous modular flyers join together in a wingtip-to-wingtip manner. Such modular flyers may derive their power from insolation. The autonomous flyers may include sensors which operate individually, or collectively after a skybase is formed. The skybase preferably may be aggregated, disaggregated, and/or re-aggregated as called for by the prevailing conditions. Thus, it may be possible to provide a “forever-on-station” aircraft. | 06-16-2011 |
20110160936 | METHOD AND DEVICE FOR ACCESSING THE DOCUMENTATION OF AN AIRCRAFT ACCORDING TO ALARMS GENERATED THEREIN - The invention in particular has as an object a method and a device for accessing the documentation of an aircraft according to alarms generated therein, the documentation comprising at least one document modifiable independently of the manufacturer of the aircraft. After having received ( | 06-30-2011 |
20110160937 | METHOD AND DEVICE FOR CENTRALIZED MANAGEMENT OF TASKS TO BE CARRIED OUT BY A CREW OF AN AIRCRAFT DURING FLIGHT - The present invention relates to a method and a device for centralized management of tasks to be carried out by a crew in the course of an aircraft flight. The method uses onboard navigation aid systems, such as a flight management system, a system for managing in-flight alerts for the implementation of the following steps: creation of a task by the flight management system; scheduling of the tasks by a system for managing alerts; and task execution by the system for managing alerts. | 06-30-2011 |
20110160938 | DEVICE FOR CENTRALIZED MANAGEMENT OF TASKS TO BE CARRIED OUT BY A CREW OF AN AIRCRAFT - The present invention relates to a device for centralized management of tasks to be carried out by a crew of an aircraft. A task to be carried out includes a triggering condition and an instruction to be executed. The device includes a man-machine interface for managing tasks by the crew, a module for creating, modifying, deleting tasks, a module for triggering a task, a module for acknowledging a task performed, a module for executing a task, and an interface with systems of the aircraft which are able to create and to execute tasks. The invention applies to the piloting tasks carried out by the pilots of an aircraft. | 06-30-2011 |
20110172853 | METHOD AND DEVICE FOR ATTENUATING THE EFFECTS OF TURBULENCE ON AN AIRCRAFT - A method for attenuating effects of turbulence on an aircraft, and a device to implement the method, the method including: using at least one signal on a wind profile signal, along an excitation direction, representing, at a given moment in an aircraft referential, a component along the excitation direction of the wind speed at a front of the aircraft according to a distance along a longitudinal direction of the aircraft; carrying out a frequency determination, in which the wind profile signal is processed to determine a frequential content; and selecting a control strategy to be adopted according to the previously determined frequential content, the strategy enabling at least one applicable control law to be identified. | 07-14-2011 |
20110178658 | SYSTEMS AND METHODS FOR MONOCULAR AIRBORNE OBJECT DETECTION - Systems and methods for airborne object detection using monocular sensors are provided. In one embodiment, a system for detecting moving objects from a mobile vehicle comprises: an imaging camera; a navigation unit including at least an inertial measurement unit; and a computer system coupled to the image camera and the navigation unit. The computer system executes an airborne object detection process algorithm, and calculates a transformation between two or more image frames captured by the imaging camera using navigation information associated with each of the two or more image frames to generate a motion compensated background image sequence. The computer system detects moving objects from the motion compensated background image sequence. | 07-21-2011 |
20110184591 | SYSTEM AND METHOD FOR DETERMINING CHARACTERISTIC PARAMETERS IN AN AIRCRAFT - The present invention provides a method and a calculation system for an aircraft, with at least one sensor for detecting aeroelastic and flight-mechanical momenta of the aircraft, for detecting positions and movements of control surfaces of the aircraft or for detecting speeds of gusts of wind acting on the aircraft and comprising a calculation unit which calculates characteristic quantities of passenger comfort and cabin safety as well as momenta of the aircraft as a function of the sensor data provided by the sensors and a non-linear simulation model of the aircraft. | 07-28-2011 |
20110190963 | METHOD AND SYSTEM FOR AN OPTIMIZED UTILIZATION OF ENERGY RESOURCES OF AN ELECTRICAL SYSTEM - A method for optimized utilization of available energy resources/sources ( | 08-04-2011 |
20110190964 | TURNING-STABILIZED ESTIMATION OF THE ATTITUDE ANGLES OF AN AIRCRAFT - The present invention relates to estimating the attitude angles of an aircraft ( | 08-04-2011 |
20110190965 | System and Method for an Integrated Backup Control System - Embodiments of the invention relate to a flight control system for controlling an aircraft in flight having a backup control system integrated into an active control stick. The actuated control stick may include a processing unit that includes independent and separate hardware and/or software dedicated to the primary control system and the backup control system. For the primary control system, the processing unit may receive a sensed primary control stick signal and communicate with a primary processor, which may be configured to generate a primary control signal. For the backup control system, the processing unit may receive a sensed backup control stick signal and generate a backup control signal. The processing unit may also generate tactile signal for use by the actuated control stick to adjust the feel of a pilot's control stick. | 08-04-2011 |
20110190966 | Control System For An Aircraft Propeller Drive - The invention relates to a control system for an aircraft propeller drive for controlling the power of a diesel engine ( | 08-04-2011 |
20110202204 | System and Method of Navigation based on State Estimation Using a Stepped Filter - Embodiments include systems and methods of navigation. In on embodiment, a plurality of position and motion states of a vehicle are estimated. The states may be estimated based on information received from a satellite receiver and an inertial measurement sensor. Estimating the states comprises performing one or more of a plurality of update steps at the rate that information is received from the satellite receiver. The states are estimated at a rate greater than the rate at which the update steps are performed. In one embodiment, the states are estimated using a stepped extended Kalman filter. | 08-18-2011 |
20110202205 | SYSTEM AND METHOD FOR DISPLAYING CONTROL RELATED INFORMATION TO AN AIRCRAFT OPERATOR - A system for displaying throttle settings to an aircraft operator includes, but is not limited to, a display unit, a data storage unit configured to store aircraft and airport data, an operator input unit configured to receive thrust related information from the aircraft operator, an aircraft sensor configured to detect an aircraft condition, and a processor. The processor is communicatively connected to each of the above components and is configured to obtain therefrom the aircraft data, the airport data, the thrust related information, and the aircraft condition. The processor is also configured to calculate a first thrust requirement based on the aircraft data, the airport data, the thrust related information, and the aircraft condition, and to provide commands to the display unit to display either the first thrust requirement. | 08-18-2011 |
20110202206 | SYSTEM AND METHOD FOR INFORMING AN AIRCRAFT OPERATOR ABOUT A TEMPORARY FLIGHT RESTRICTION IN PERSPECTIVE VIEW - A system for informing aircraft operators about a temporary flight restriction (“TFR”) includes, but is not limited to, a display unit that is adapted for attachment to an aircraft. The display unit is configured to display graphical images. A processor is communicatively connected to the display unit and is configured to control the display unit. A receiver is communicatively connected to the processor and is configured to receive a broadcast containing information relating to the TFR (“TFR information”) and to automatically provide the TFR information to the processor. The processor is further configured to automatically control the display unit to display a three dimensional representation of an airspace that is subject to the TFR relative to the position of the aircraft when the processor receives the TFR information from the receiver. | 08-18-2011 |
20110213513 | METHOD FOR AUTOMATIC AVOIDANCE OF COLLISIONS BETWEEN A CRAFT AND FURTHER OBJECTS - A method for controlling the motion of an object for the avoidance of collisions with obstacles includes: detecting of at least one non-stationary or stationary obstacle; defining a safety zone around the obstacle which moves together with the obstacle; detecting whether the obstacle, including its safety zone, is in a collision course with the object; calculating an avoidance trajectory, which by-passes the obstacle, such that the avoidance trajectory, at least approximately, is circularly shaped and that the circularly-shaped avoidance trajectory, or a straight line tangentially linked thereto, is tangent to the safety zone around the obstacle; and driving the object such that it follows, at least approximately, the calculated avoidance trajectory, whereby the calculated avoidance trajectory is tangentially linked to the previous trajectory. | 09-01-2011 |
20110224846 | METHOD FOR ACTIVELY DEFORMING AN AERODYNAMIC PROFILE - The present invention relates to a method for actively deforming, by feedback control, an aerodynamic profile comprising an elastic material, applied to a part of the surface of the aerodynamic profile, said elastic material being in contact with a fluid flow; said elastic material being able to be deformed by one or more shape memory actuators placed in contact with the elastic material, said actuators being controlled by a computer connected to sensors. This method applies notably to a deformation of an aerofoil of a wing of an aircraft in flight, notably subsonic. | 09-15-2011 |
20110231036 | AIRCRAFT COMMUNICATIONS RADIO TUNING AID SYSTEM AND METHOD - Methods and apparatus are provided of displaying air traffic control communication information in an aircraft having an aircraft communications radio. Each air traffic control (ATC) communication station that is within a predetermined distance of an aircraft position is identified. Indicia representative of the identified ATC communication stations that are determined to be within the range of the aircraft communications radio are rendered on a display device. | 09-22-2011 |
20110238239 | Single Processor Class-3 Electronic Flight Bag - An electronic flight bag providing computational services for an aircraft and communicating with aircraft avionics may execute aircraft-design-approved Type-C applications together with non-design-approved Type-A/B on a single processor through specific modifications of the operating system to control memory and processor access thereby providing isolation comparable to that of dual processor systems in which the Type-C applications and Type-A/B applications are executed on different processors. | 09-29-2011 |
20110245999 | AIRCRAFT HEALTH MONITORING AND DESIGN FOR CONDITION - A system and method for automatically varying the flight envelope of an aircraft based upon the material health of the aircraft and the flight environment is provided. The system includes a plurality of structural health monitoring and load sensors that determine the approximate size and the approximate location of the damage. The system performs residual strength calculations for individual aircraft components to determine the overall aircraft residual strength. The system uses these calculations to determine a maximum flight envelope based on the overall aircraft residual strength, and transmits this information to the flight controller and optionally to the pilot. | 10-06-2011 |
20110251739 | DISTRIBUTED FLY-BY-WIRE SYSTEM - A system includes a plurality of fly-by-wire control units to control flight control surfaces of an airplane, wherein each control unit is adapted to operate independently of other control units and directly control an actuator to control a control surface as a function of direct pilot control device input. | 10-13-2011 |
20110264307 | GNSS OPTIMIZED AIRCRAFT CONTROL SYSTEM AND METHOD - A GNSS system in combination with a hydraulically-actuated, airborne dispenser for a dry material crop dusting system to optimize the distribution of dry materials over a particular tract of land. A GNSS subsystem is included using at least one GNSS antenna and one GNSS receiver located on the aircraft. The aircraft is equipped with an electronic/hydraulic crop dusting subsystem connected to a GNSS CPU. The GNSS ranging signals received by the antennas are processed by a receiver and processor system for determining the vehicle's position and dynamic attitude in three dimensions (3D). A graphical user interface (GUI) placed in the vehicle will give the driver a real-time view of his or her current bearing as well as a calculated “optimal path” based on calculations and variable data, such as wind speed and direction, material moisture content, altitude, air speed and other conditions. The system is adapted for operation in a differential GNSS (DGNSS) mode utilizing a base station at a fixed location. | 10-27-2011 |
20110270469 | UNIVERSAL MOUNTING SYSTEM FOR A HANDHELD ELECTRONIC DEVICE - A universal mounting system for a handheld electronic device includes a handheld electronic device, a first mounting plate, and a second mounting plate. The handheld electronic device includes universal mounting members operable to mount to mounting plates. The first mounting plate includes first receiving members operable to detachably couple to the universal mounting members of the handheld electronic device. The first mounting plate also includes a fastener assembly operable to detachably couple the first mounting plate to a person. The second mounting plate includes second receiving members operable to detachably couple to the universal mounting members of the handheld electronic device. The second mounting plate also includes a connector assembly operable to attach the second mounting plate to a vehicle. | 11-03-2011 |
20110270470 | AIRCRAFT SYSTEMS AND METHODS WITH ACTIVE DECELERATION CONTROL - A system is provided for controlling the speed of an aircraft during a deceleration segment between a first state associated with a first speed and a first time and a second state associated with a second speed and a second time. The system includes a navigation system configured to determine the first state; a guidance system configured to determine the second state; and an active deceleration system coupled to the navigation system and the guidance system and configured to construct the deceleration segment between the first state and the second state with at least one intermediate speed between the first speed and the second speed. | 11-03-2011 |
20110270471 | Control Panel For An Aircraft - The control panel ( | 11-03-2011 |
20110276198 | VERTICAL PROFILE DISPLAY WITH VARIABLE DISPLAY BOUNDARIES - A display system includes instrumentation configured to obtain aircraft data comprising current flight status data of the host aircraft and current flight status data of neighboring aircraft located near the host aircraft. The system also includes a processor coupled to the instrumentation. The processor analyzes and filters the aircraft data, using lateral boundary criteria for the host aircraft, to identify a proper subset of the neighboring aircraft, and the processor generates image rendering display commands based upon the current flight status data of the host aircraft and based upon the current flight status data of neighboring aircraft included in the proper subset. A display element receives the image rendering display commands and, in response thereto, renders a vertical situation display that includes graphical representations of the host aircraft and each neighboring aircraft included the proper subset. | 11-10-2011 |
20110276199 | FLIGHT CONTROL SYSTEM AND AIRCRAFT COMPRISING IT - A flight control system for an aircraft, in which control commands are transmitted between a flight control module ( | 11-10-2011 |
20110282521 | Aviation Application Setting Antenna Array and Integrated Temperature Sensor - An antenna array for use in an aviation application setting comprises an external covering and at least four radio frequency antennas that are disposed underneath and that are protected by the external covering. A deposit of phosphor material is also disposed beneath this covering. This external covering is at least partially permeable to radio frequency signals and will provide at least a substantial barrier against external moisture and objects that might otherwise harm the antennas. This external covering can be fixed to an exterior surface of an aircraft. The four radio frequency antennas are electrically discrete from one another though also being configured as an integral mechanical structure. The phosphor material, in turn, can serve to facilitate detection of a parameter of interest, such as temperature or airspeed. | 11-17-2011 |
20110295448 | SYSTEM ABOARD AN AIRCRAFT - The invention relates to a device aboard an aircraft comprising output means ( | 12-01-2011 |
20110307125 | METHOD OF MONITORING THE EFFECTIVENESS OF A DAMPER, AND A DEVICE FOR IMPLEMENTING SAID METHOD - The present invention relates to a method of monitoring the effectiveness of a damper system, wherein the method consists in measuring the relative movements of two strength members, in filtering the measurements in order to isolate those that relate to the lead-lag resonant frequency of the blade, in rectifying the signal, in recording the signal, in comparing the rectified signal (S) with a threshold value (S | 12-15-2011 |
20110313597 | METHODS AND SYSTEMS FOR DISPLAYING ANNOTATIONS ON AN AIRCRAFT DISPLAY - Methods and systems are provided for presenting content on a display device onboard an aircraft. A method comprises displaying, on the display device, information corresponding to a first procedure and displaying an annotation associated with the first procedure on the display device. The first procedure is associated with an airport and prescribes operation of the aircraft in a vicinity of the airport, and the annotation comprises user-defined information pertaining to the first procedure. | 12-22-2011 |
20110313598 | METHOD AND SYSTEM FOR DYNAMICALLY MANAGING A FLIGHT PROCEDURE OF AN AIRCRAFT FLIGHT PLAN - A method of managing a flight procedure of an aircraft flight plan, which has at least one segment, includes a step in which an additional attribute of the segment representative of a compulsory or optional nature of the flight of said segment is dynamically selected. | 12-22-2011 |
20110313599 | AIRCRAFT BACKUP CONTROL - A system is disclosed for controlling an aircraft when the hydraulic system of the aircraft has been compromised. The system includes a digital fly-by-wire control system configured to rescale at least one gain vector. The gain(s) may then used by a digital control to modulate engine thrust. In this manner, engine thrust modulation may be used for stabilization and control of control-configured aircraft without requiring a substantial change in piloting technique. | 12-22-2011 |
20120010765 | SYSTEM FOR DISPLAYING A PROCEDURE TO AN AIRCRAFT OPERATOR DURING A FLIGHT OF AN AIRCRAFT - A system is disclosed for displaying a procedure to an aircraft operator during a flight of an aircraft. The system includes, but is not limited to, a display unit, a data storage unit that is configured to store the procedure, an input unit, and a processor that is communicatively connected to the display unit, to the data storage unit and to the input unit. The processor is configured to obtain the procedure from the data storage unit, to receive an input from the input unit, and to control the display unit to display the procedure as a vertical profile having a compressed portion and an expanded portion, the expanded portion corresponding to the input. | 01-12-2012 |
20120016537 | System and Method for Detection of Anti-Satellite Vulnerability of an Orbiting Platform - A system and method for detection of anti-satellite vulnerability of an orbiting platform. An engagement volume processing unit receives a maximum impulse velocity of an SBI launched from a carrier platform of interest, a maximum time of flight (TOF) until intercept, and orbital data of the carrier platform of interest. A family of interceptor imparted velocities in a VNC frame is determined. The engagement volume processing unit applies the family of velocities over “N” release points using a carrier platform propagator to determine an engagement volume. A display and alert processing unit generates a visual representation of the engagement volume and sends the visual representation to the display device for display. | 01-19-2012 |
20120016538 | UAV POWER LINE POSITION AND LOAD PARAMETER ESTIMATION - A system and method for providing autonomous navigation for an Unmanned Air Vehicle (UAV) in the vicinity of power lines is presented. Autonomous navigation is achieved by measuring the magnitude and phase of the electromagnetic field at an unknown location within a space under excitation by a set of power cables of the power line with one or more orthogonal electromagnetic sensors formed on the UAV; modeling a set of expected complex electromagnetic strengths of the set of power cables at the currently estimated position and orientation of the UAV based on a model of the set of power cables; and estimating parameters related to a position and orientation of the UAV, and load parameters of each cable based on the residual error between the measured set of complex electromagnetic field values and the set of expected electromagnetic field values corresponding to a combined model of the set of power cables. | 01-19-2012 |
20120022720 | METHOD AND DEVICE FOR PROTECTING SOFTWARE COMMANDS IN AN AIRCRAFT COCKPIT - The invention in particular has as an object the control of execution of software commands of a data-processing system in an aircraft cockpit comprising means for allowing a user to call up these commands. For these purposes, the means making it possible to call up these commands initially are locked ( | 01-26-2012 |
20120022721 | FLYING OBJECT - By using the interaction between the wind flow and the stabilizer arranged in the wind flow and along the direction of the wind flow, this invention provides the flying object that secures the stability of device or aircraft or stabilizer itself unified with the stabilizer by above effect. The interaction mentioned above is that when the wind flow hits the stabilizer at a certain angle, the wind flow changes the direction, and the power corresponding its reaction is given to the stabilizer by its reaction. | 01-26-2012 |
20120022722 | SYSTEMS, METHODS, AND APPARATUS FOR OTOACOUSTIC PROTECTION OF AUTONOMIC SYSTEMS - Systems, methods and apparatus are provided through which in some embodiments an autonomic unit transmits an otoacoustic signal to counteract a potentially harmful incoming signal. | 01-26-2012 |
20120029735 | METHOD AND SYSTEM FOR VERTICAL NAVIGATION USING TIME-OF-ARRIVAL CONTROL - A method and systems for controlling an aircraft during descent are provided. The control system includes an input device configured to receive a speed margin for the vehicle and a processor communicatively coupled to the input device wherein the processor is programmed to automatically determine a flight path of the vehicle that is shallower than an idle flight path for the vehicle and generate a flight control surface control signal configured to maintain the determined flight path using the received speed margin. The control system further includes an output device communicatively coupled to the processor. The output device is configured to transmit the flight control surface control signal to a flight control system of the vehicle. | 02-02-2012 |
20120029736 | Method for Dynamically Consolidating Items of an Aeronautical Procedure - A method is provided for dynamically consolidating items of an aeronautical procedure in order to present to the operator the best action to perform according to the context of all the systems, in order to reduce his cognitive workload faced with an action to be carried out. The method consists, for each item of a procedure, in determining the text of the requested action, in choosing the text of the corresponding response that the crew must perform according to the general state and the configuration of the aircraft, in incorporating in the corresponding item the texts of the requested action and of the corresponding response, in displaying this duly enriched item, in detecting whether the requested action has indeed been accomplished and in displaying the result of this detection. | 02-02-2012 |
20120029737 | CENTRALIZED NAVIGATION INFORMATION MANAGEMENT METHOD AND SYSTEM - In a centralized navigation information management system installed on board an aircraft which is in a current position at a current time, the aircraft having a warning management system and a route management system with means for creating a route plan, the route plan having a future route plan corresponding with the part of the route plan beginning at the current position and at the current time, the system includes: means for creating a task comprising at least one task parameter relating to an item of navigation information, including a task variable corresponding to a condition of execution of the said task, the means for creating a task having means for determining a predicted time meeting the execution condition; and means for detecting a possible inconsistency between the created task and the route plan or the future route plan and for transmitting, when an inconsistency is detected, a message relating to the inconsistency to a first display means of a centralized warning management system to display the inconsistency message on a first man-machine interface. | 02-02-2012 |
20120035787 | LAYERED ARCHITECTURE FOR CUSTOMER PAYLOAD SYSTEMS - A layered architecture for customer payload systems is disclosed to provide a scalable, reconfigurable integration platform targeted at multiple unmanned aerial vehicles (UAV), and remove both UAV specific and payload equipment specific characteristics that increase complexity during integration. The layered architecture is a modular design architecture that is split by function. Standard interfaces are implemented between functional layers to increase reconfiguration possibilities and to allow reuse of existing components and layers without modification to the payload or UAV. The standard interfaces also promote easy connection and disconnection from other layer components. Additionally, once the layered architecture is implemented, technological or functional requirements changes can be isolated to one specific component layer, not the entire payload stack. As a result, payload designs based on the layered architecture reduces design time and cost, and allows for easier integration, operation, upgrades, maintenance, and repair. | 02-09-2012 |
20120035788 | NAVIGATION AND CONTROL SYSTEM FOR AUTONOMOUS VEHICLES - A navigation and control system including a sensor configured to locate objects in a predetermined field of view from a vehicle. The sensor has an emitter configured to repeatedly scan a beam into a two-dimensional sector of a plane defined with respect to a first predetermined axis of the vehicle, and a detector configured to detect a reflection of the emitted beam from one of the objects. The sensor includes a panning mechanism configured to pan the plane in which the beam is scanned about a second predetermined axis to produce a three dimensional field of view. The navigation and control system includes a processor configured to determine the existence and location of the objects in the three dimensional field of view based on a position of the vehicle and a time between an emittance of the beam and a reception of the reflection of the emitted beam from one of the objects. | 02-09-2012 |
20120041619 | System for Aircraft - This invention relates to a sensing system with networking capabilities that is integrated into an aircraft that allows for rapid reconfiguration, monitoring, and access control of the aircraft by way of using fastening mechanisms, namely those with intelligent capabilities that provide sensing, control, and monitoring capabilities. | 02-16-2012 |
20120041620 | SYSTEMS AND METHODS FOR PROVIDING SPOOF DETECTION - Spoof detection can be performed by various systems and methods. The systems and methods can provide for detection by passive listening, active interrogation, and other techniques. Moreover, systems and methods can also provide for reporting and displaying information relating to detected spoofing. For example, a method can include receiving, on a device, a signal providing a report for an aircraft. The method can also include determining, with the device, a first parameter for the aircraft from information in the report. The method can further include determining, with the device, a second parameter for the aircraft from at least one signal characteristic of the signal. The method can additionally include determining, with the device, a validity status of the report based on comparing the first parameter and the second parameter. | 02-16-2012 |
20120046810 | FUZZY LOGIC-BASED CONTROL METHOD FOR HELICOPTERS CARRYING SUSPENDED LOADS - The fuzzy logic-based control method for helicopters carrying suspended loads utilizes a controller based on fuzzy logic membership distributions of sets of load swing angles. The anti-swing controller is fuzzy-based and has controller outputs that include additional displacements added to the helicopter trajectory in the longitudinal and lateral directions. This simple implementation requires only a small modification to the software of the helicopter position controller. The membership functions govern control parameters that are optimized using a particle swarm algorithm. The rules of the anti-swing controller are derived to mimic the performance of a time-delayed feedback controller. A tracking controller stabilizes the helicopter and tracks the trajectory generated by the anti-swing controller. | 02-23-2012 |
20120059535 | SYSTEMS AND METHODS FOR RTA CONTROL OF MULTI-SEGMENT FLIGHT PLANS WITH SMOOTH TRANSITIONS - Methods, systems and device are provided for smoothing a required time of arrival (RTA) speed transition for an aircraft in a multi-segmented speed profile including at least one preceding region with a first predetermined speed pad and at a speed constrained region with a second predetermined speed pad. Exemplary methods include, but are not limited to determining whether a speed constrained region is engaged by a preceding region based at least in part on a speed of an aircraft. If the speed constrained region is engaged, the instructions determine a revised second speed pad for the speed constrained region. If the speed constrained region is not engaged then the instructions assign a default speed pad as the second speed pad for the speed constrained region. The instructions also compile a new speed profile that is defined by one of the revised second speed pad and the default speed pad for the speed constrained region and transmit commands that accelerate the aircraft to a new speed based on the new speed profile. | 03-08-2012 |
20120065816 | SYSTEMS AND METHODS FOR DYNAMICALLY STABLE BRAKING - Systems and methods for dynamically stable braking are disclosed. A first electromechanical brake actuator controller may be placed in communication with a second electromechanical brake actuator controller, wherein each of the first electromechanical brake actuator controller and second electromechanical brake actuator controller are in communication with electromechanical brake actuators that are associated with the same wheel. The first electromechanical brake actuator controller and second electromechanical brake actuator controllers may then communicate electromechanical brake actuator status information and take corrective measures in accordance with the status information. | 03-15-2012 |
20120072056 | FLIGHT CONTROL SYSTEM FOR ROTARY WING AIRCRAFT - A flight control system and method includes a control loop control law to bias the collective stick toward a trim reference position with a motor and generate a force gradient with a clutch. | 03-22-2012 |
20120072057 | METHOD OF MANAGING MOVEMENT OF AN AIRCRAFT ON THE GROUND - The invention relates to a method of managing movement of an aircraft on the ground, the aircraft including at least one left main undercarriage and at least one right main undercarriage, each comprising wheels associated with torque application members for applying torque to the wheels in response to a general setpoint, the general setpoint comprising a longitudinal acceleration setpoint and an angular speed setpoint, the method including the successive steps of braking down the general setpoint into general torque setpoints for generating by the torque application members associated with each of the wheels. | 03-22-2012 |
20120072058 | Pilotless Aircraft for Commercial and Military Use - An aircraft control system is described having an Automatic Monitoring System (“AMS”), an Aircraft Parameter Management Computer (“APC”), and a Flight Management Computer (“FMC”) to monitor the parameters of the aircraft automatically and to fly the aircraft without requiring a pilot to fly. The system respond to data within the systems and with data provided by a communication/navigation aid of the airport. The built-in systems of the aircraft process the data to allow pilotless operation of the aircraft along a predetermined route while maintaining proper spacing from prior art and other automated aircraft. An aircraft in accordance with the invention utilizes programmed software, electronics circuit and feedback system to fly the aircraft within the designated/destined routes and airports automatically while providing increased security by preventing accidents caused by incorrect or unauthorized human influence. | 03-22-2012 |
20120078445 | COMPUTER ASSISTED HUMAN MACHINE INTERFACE DISPLAY - Methods and apparatus are provided for selectively balancing pilot workload. The apparatus comprises a display device configured to display a user interface (UI) and a processor. The processor is configured to determine a state of the pilot and/or a state of the aircraft, prepare modification to the UI based in part on the state of the pilot and/or the state of the aircraft such that the modification adds one or more command icons without obscuring, without removing, and without replacing any information item on the display, and to execute the modification. | 03-29-2012 |
20120078446 | Integrated Upsampler and Filtering for Multi-Rate Controller for Electro-Mechanical Flight Actuation System - Presented is a system and method for controlling an actuator in a multirate control system using an integrated upsampler and filter, comprising an incremental command limiter for changing a command from a first control system into a limited incremental command in a second control system, a lead-lag filter for filtering the limited incremental command to attenuate high frequencies, and a feed forward path for reducing phase loss in rate output signal at low frequencies. In embodiments, a command position signal received at the sampling rate of the first control system is interpolated into incremental command position signals at the sampling rate of the second control system. Position error signals and rate error signals from the devices being controlled are used as feedback to further stability the control loops. | 03-29-2012 |
20120078447 | AUTOMATIC PRESENTATION OF A SHORTCUT PROMPT TO VIEW A DOWNLINK REQUEST MESSAGE RESPONSIVE TO A CONFIRM-RESPONSE MESSAGE - A system to reduce head-down time for a flight crew is provided. The system includes a functional module including a set of screens used to receive and send controller pilot data link communications (CPDLC) messages between an aircraft and a ground system; a message composition screen communicatively coupled to the functional module; and a shortcut interface communicatively coupled to the functional module, wherein a shortcut prompt is automatically displayed when a confirm-response message received responsive to a previously-sent downlink request message is viewed, and wherein the previously-sent downlink request message is displayed when the shortcut interface is implemented. | 03-29-2012 |
20120078448 | MIXED-INTIATIVE TRANSFER OF DATALINK-BASED INFORMATION - A system and method are provided for transferring datalink-based information into an aircraft flight management system. When a datalink message is received in an aircraft, it is parsed into individual information elements. The operational impact of the received datalink message on the aircraft is determined from the individual information elements. A method of supplying pilot feedback regarding the received datalink message is determined from the determined operational impact. The pilot feedback regarding the received datalink message is supplied using the determined method. At least selected portions of the individual information elements are selectively transferred into the aircraft flight management system (FMS). | 03-29-2012 |
20120078449 | AUTOMATICALLY AND ADAPTIVELY CONFIGURABLE SYSTEM AND METHOD - Methods and apparatus are provided for automatically and adaptively configuring a system for a user. User data that includes information representative of temporal and contextual user preferences, behaviors, habits, biases, idiosyncrasies, and tendencies associated with system settings and configurations are loaded into the system. The system is then configured based on the user data. User-initiated operations of the system are continuously monitored to model user performance. The user data are continuously updated based on the modeled user performance, and the system is continuously and automatically reconfigured based on the updated user data. | 03-29-2012 |
20120083946 | TAILORED ARRIVALS ALLOCATION SYSTEM TRAJECTORY PREDICTOR - The different advantageous embodiments provide a system for generating trajectory predictions for a flight comprising a flight object manager and a trajectory predictor. The flight object manager is configured to generate flight information using a number of flight plans, a number of flight schedules, and flight status information. The trajectory predictor is configured to receive flight information from the flight object manager and use the flight information to generate the trajectory predictions. | 04-05-2012 |
20120083947 | INTEGRATED FRAMEWORK FOR VEHICLE OPERATOR ASSISTANCE BASED ON A TRAJECTORY AND THREAT ASSESSMENT - Various types and levels of operator assistance are performed within a unified, configurable framework. A model of the device with a model of the environment and the current state of the device and the environment are used to iteratively generate a sequence of optimal device control inputs that, when applied to a model of the device, generate an optimal device trajectory through a constraint-bounded corridor or region within the state space. This optimal trajectory and the sequence of device control inputs that generates it is used to generate a threat assessment metric. An appropriate type and level of operator assistance is generated based on this threat assessment. Operator assistance modes include warnings, decision support, operator feedback, vehicle stability control, and autonomous or semi-autonomous hazard avoidance. The responses generated by each assistance mode are mutually consistent because they are generated using the same optimal trajectory. | 04-05-2012 |
20120089277 | VARIABLE GAIN CONTROL NOSE WHEEL STEERING SYSTEM - A method for determining a target steering angle for nose landing gear of an aircraft includes receiving rudder pedal input data into a steering control unit, receiving aircraft speed data into the steering control unit, calculating a normal gain, calculating a parking gain, and adding the normal gain and the parking gain to determine the target steering angle. The normal gain is a positive quantity in all aircraft speed and pedal stroke ranges. The parking gain is a positive quantity in parking and taxiing speed ranges. A nose wheel steering system is also disclosed. | 04-12-2012 |
20120095621 | TRAJECTORY TRACKING FLIGHT CONTROLLER - A six degree-of-freedom trajectory linearization controller (TLC) architecture ( | 04-19-2012 |
20120095622 | SYSTEMS AND METHODS FOR ENERGY CONSERVING WIRELESS SENSING WITH SITUATIONAL AWARENESS - A system and method is provided for monitoring aircraft health and status using a situation-aware sensing system. The system includes an independent power source, a sensor that continuously measures a signal of interest to yield sensor data, and a processor that compares the sensor data to threshold data. The processor adjusts an operational parameter of the situation-aware sensing system to conserve power when the sensor data does not exceed the threshold data. The processor further adjusts the operational parameter of the situation-aware sensing system to stop conserving power when the sensor data exceeds the threshold data. | 04-19-2012 |
20120101663 | DISTRIBUTED FLIGHT CONTROL SYSTEM IMPLEMENTED ACCORDING TO AN INTEGRATED MODULAR AVIONICS ARCHITECTURE - A flight control system for an aircraft, intended for controlling a plurality of actuators adapted for actuating control surfaces of the aircraft from information supplied by piloting members and/or sensors of the aircraft. The system includes a primary control system adapted for controlling a first set of control surface actuators and a secondary control system adapted for controlling a second set of control surface actuators, the primary and secondary systems being respectively powered by independent energy sources of different types. | 04-26-2012 |
20120101664 | Method of Controlling Steering Control Equipment for Aircraft, and Steering Control Equipment for Aircraft and Aircraft Provided Therewith - A steering control equipment has a controller having a provisional-target-angular-position calculating section calculating a provisional target angular position of a steering mechanism corresponding to the operation amounts of a steering handle and rudder pedals, a speed setting section setting the aircraft speed on the basis of detected ground speed and airspeed, a target-angular-position limiting section outputting the provisional target angular position as a final target angular position when the calculated provisional target angular position is equal to or lower than a limit value corresponding to the set speed and outputting the limit value as a final target angular position when the calculated provisional target angular position is larger than the limit value, and a actuating control section controlling an actuating mechanism for actuating the steering mechanism so that the output final target angular position and the actual angular position of the steering mechanism detected coincide with each other. | 04-26-2012 |
20120101665 | VEHICLE INTERFACE BASED ON THE WEIGHT DISTRIBUTION OF A USER - In one embodiment, the invention is an interface for communicating a vehicle command from a user to a vehicle. The interface preferably includes a support system to support at least a portion of the weight of a user, a sensor system to sense the weight distribution of the user, and a processor to interpret a vehicle command based on the weight distribution of the user and to communicate the vehicle command to a vehicle. | 04-26-2012 |
20120101666 | Aircraft Occupant Protection System - An occupant protection system for an aircraft comprising a sensor system for sensing flight condition information and a control system, which includes an impending crash detection system and an impact detection system. The impending crash detection system receives flight information from the sensors determines whether a crash is likely to occur. If an impending crash is detected, the impending crash detection system activates impact modes of a first group of aircraft systems. The impact detection system receives flight information from the sensor system and determines whether an impact has occurred or is occurring. If an impact is detected, the impact detection system activates impact modes of a second group of aircraft systems. | 04-26-2012 |
20120109424 | AIRCRAFT CONTROL SYSTEM WITH INTEGRATED MODULAR ARCHITECTURE - An aircraft control system in which a plurality of elementary control systems, corresponding to different aircraft functions, can share one or more sensors due to a common AFDX network. The transmission of commands is carried out via AFDX messages sent to network-subscribed actuators. Advantageously, the computers of the different elementary control systems installed in the avionics bay include generic computers hosting software specific to execution of respective functions thereof (IMA architecture). | 05-03-2012 |
20120116610 | AUTOMATIC CONTROL OF AN AIRCRAFT IN THE EVENT OF FLIGHT CREW INCAPACITY - A method for automatic control of an aircraft in event of flight crew incapacity may include determining any incapacity of the flight crew. The method may also include providing a message requiring acknowledgement from the flight crew in response determining incapacity of the flight crew. The method may additionally include commanding an auto pilot to control the aircraft in response to not receiving acknowledgement from the flight crew. | 05-10-2012 |
20120116611 | Managing Control Surfaces for an Aircraft - A method and apparatus for managing a number of control surfaces for an aircraft. A current configuration for the number of control surfaces for the aircraft is identified during flight of the aircraft. A selected point in time at which the current configuration for the number of control surfaces is to be changed to a new configuration for the number of control surfaces is identified. A portion of time relative to the selected point in time during which the current configuration for the number of control surfaces is to be changed to the new configuration is identified based on a difference between a current amount of energy for the aircraft and an expected amount of energy for the aircraft. | 05-10-2012 |
20120116612 | IMPLEMENTATION OF KALMAN FILTER LINEAR STATE ESTIMATOR FOR ACTUATOR EQUALIZATION - A rotorcraft control system is provided and includes a rotor blade having a moving surface operatively connected for movement among various positions, an actuator receptive of a modified control signal and operatively connected to move the surface among the various positions, a sensor operably coupled to the actuator to generate a sensor response signal reflective of a response of the actuator to the modified control signal and a controller to output the modified control signal to the actuator, the controller including a control loop to generate the modified control signal from an initial control signal that is modified by relating the initial control signal and the sensor response signal and by accounting for actuator inaccuracies, sensor sensitivities and noise. | 05-10-2012 |
20120116613 | METHOD OF CONTROLLING AN OVERSPEED SAFETY SYSTEM FOR AEROENGINES AND A CONTROL CIRCUIT FOR IMPLEMENTING SAID METHOD - A method of controlling an overspeed safety system for an aircraft having at least two engines. The method includes setting said overspeed safety system for the engines, monitoring the speeds of rotation of the engines, detecting overspeed on one of the engines, shutting down the engine in question in the event of detecting overspeed, and inhibiting the operation of the overspeed safety system for the other engine(s) still in operation. The method also comprises the steps of monitoring safety parameters associated with the operation and/or the shutting down of the engine that has been shut down; and maintaining the inhibition or resetting the overspeed safety system for the other engine(s) still in operation, as a function of one or more safety parameters. | 05-10-2012 |
20120116614 | METHOD AND APPARATUS FOR AIR TRAFFIC TRAJECTORY SYNCHRONIZATION - According to aspects of the embodiments, there is provided an apparatus and method to synchronize the distinct trajectories predicted by a flight management system and air navigation service provider. A comparison model is generated that indicates differences between an aircraft trajectory and a ground trajectory. The aircraft trajectory is updated to reflect identified discrepancies and restriction violations between the trajectories. Upon successful completion of the first designated change, a notification manager is used to issue a notification of the designated change to the flight plan trajectory. A modified ground trajectory is produced that incorporates the designated change to the flight plan trajectory. The comparison is repeated until the discrepancies of the trajector | 05-10-2012 |
20120116615 | Secure Terminal Data Loader Apparatus and Method for a Mobile Platform - A terminal data loading device on a mobile platform includes a media unit for receiving a transportable media element containing media data and outputting a media signal to a control processor unit. The control processor unit outputs an information signal to a wireline communication unit. The wireline communication unit outputs a wireline signal to a network on the mobile platform. | 05-10-2012 |
20120123615 | METHOD AND A SYSTEM FOR ESTIMATING A TRAJECTORY OF A MOVING BODY - A hybrid simulation method uses a simulator tool feeding kinematics commands to a movement simulator on which a moving body is mounted and to a target representative of an objective to be reached by the moving body, and on detection of an event representative of overshooting or changing a first designated objective for this moving body, the method includes a positioning stage associated with a second designated objective for the moving body, including comparing positions executed by the movement simulator in response to transition kinematics commands with a first predetermined setpoint position and activating a first marker if a position substantially the same as the first setpoint position is detected; comparing positions executed by the target in response to transition kinematics commands with a second predetermined setpoint position and activating a second marker if a position substantially the same as the second setpoint position is detected; when the first and second markers are activated, a step of evaluating a difference between the current kinematics command supplied to the movement simulator and the target by the digital simulator tool; and, if this difference is below a particular threshold, a piloting stage including applying corrective terms linked to the setpoint positions to the kinematics commands coming from the simulator tool before they are fed to the movement simulator and to the target. | 05-17-2012 |
20120123616 | SYSTEM AND METHOD FOR COMPUTING AN EQUI-TIME POINT FOR AIRCRAFTS - A system and method for generating an equi-time point (ETP) for an emergency landing of an aircraft are disclosed. In one aspect, a method of a flight management system (FMS) of an aircraft for generating an ETP for an emergency landing of the aircraft includes receiving at least two reference points for landing the aircraft upon an occurrence of an emergency. The method also includes determining an equi-distance point (EDP) for the aircraft by locating a first point on the remaining flight path of the aircraft which is equidistant from the at least two reference points. The method further includes generating an ETP for the aircraft by locating a second point on the remaining flight path such that time difference between any two of expected flight times of the aircraft from the second point to the at least two reference points is less than a threshold value. | 05-17-2012 |
20120130563 | SYSTEM AND METHOD FOR SELECTIVELY ENABLING A CONTROL SYSTEM FOR ACCESSING A CENTRAL PROCESSING UNIT - A system and method are disclosed for selectively enabling a control system using a biometric and a physiological sensor to determine the status of an operator. An input component is operatively coupled to the sensor to permit an operator to initialize the sensor. A central processor unit is operatively coupled to the operator sensor and the central processor unit has a transceiver operatively coupled therewith for processing and evaluating the biometric and physiological information: A transceiver coupled with a remote ground control; an override operatively coupled to the ground control. Alternatively, the present invention comprises a security control center, which controls the operation of at least one biometric sensor and at least on physiological sensor: the security control center also capable of detecting said normal and said abnormal sensory reading and the central processing unit in response to said sensory reading. | 05-24-2012 |
20120130564 | SYSTEM AND METHOD FOR COMPUTING AN EQUI-DISTANCE POINT (EDP) FOR AIRCRAFTS - A system and method for dynamically computing an equi-distance point (EDP) for aircrafts is disclosed. In one embodiment, a method for dynamically computing an EDP for an aircraft includes receiving at least two reference points for landing the aircraft upon an occurrence of an emergency, determining a remaining flight path for the aircraft based on a current location of the aircraft and a flight plan serviced by a flight management system (FMS) of the aircraft, and generating the EDP for the aircraft by locating a point on the remaining flight path which is equidistant from the at least two reference points. | 05-24-2012 |
20120130565 | FLIGHT CONTROL SYSTEM OF AIRCRAFT - A flight control system of an aircraft and a flight control method of the aircraft are provided in which the overrunning an operation limitation on a flight condition can be prevented even when a pilot operates a flight control device fast. The flight control system of the aircraft includes a flight control device; a sensor configured to detect a first parameter changed based on a flight condition of the aircraft; a limitation flight control position calculating section configured to calculate a limitation flight control position of the flight control device when the first parameter reaches a limitation value, based on the first parameter; a reaction force generating actuator configured to change a reaction force which the pilot receives when carrying out a flight control input to the flight control device, in response to a reaction force generating command generated based on the flight control position of the flight control device and the limitation flight control position; an inner loop command calculating section configured to generate an inner loop command based on the flight control position; and a control surface actuator configured to drive a control surface of the aircraft based on the flight control position and the inner loop command. | 05-24-2012 |
20120136512 | External Load Inverse Plant - A method of controlling the flight of a rotorcraft in a feed-forward/feedback architecture includes utilizing an aircraft plant model to control the rotorcraft performance; determining when an external load is coupled to the rotorcraft; and modifying an inverse plant when the external load is present. | 05-31-2012 |
20120136513 | Accelerometer autopilot system - The Accelerometer Autopilot System is an airplane and helicopter autopilot system that functions by a specially programmed software. The computer program directs aircraft navigation using accelerometer generated coordinates of altitude, latitude, longitude and distance travelled. The system uses four accelerometers that are specifically aligned by a solid-state compass to True North. Using fundamental Dynamics equations, the accellerations or decellerations are timed by an atomic clock and converted into velocities and distances. The distances are then either added to or subtracted from the departure point coordinates to obtain the new position coordinates. These new position coordinates will identify the real-time position of the aircraft as it is flying. When these coordinates are recorded during a programming flight the autopilot will track these coordinates as will be shown on the dashboard display screen. The pre-recorded coordinate course and the course azimuth will guide the aircraft to the destination point. This is accomplished without the use of gyros, GPS, or a VOR radio signal. | 05-31-2012 |
20120143405 | DATA SYNCHRONISATION FOR A FLIGHT INFORMATION SYSTEM | 06-07-2012 |
20120143406 | Aircraft Avionics System - An aircraft avionics system ( | 06-07-2012 |
20120150364 | UNMANNED VEHICLE AND SYSTEM - An unmanned vehicle is provided. The unmanned vehicle includes a navigation system configured to navigate the unmanned vehicle relative to a beam of energy emitted from a beam source, a power receiver configured to receive energy from the beam, and an energy storage system configured to store received energy for use in selectively powering the unmanned vehicle. | 06-14-2012 |
20120150365 | Wireless Precision Avionics Kit - A wireless precision avionics kit is provided for retrofitting aircraft to facilitate communication between the cockpit and modern military stores without hardware or software modifications to the aircraft. The store includes an electrical interface that requires data and possibly power from the aircraft and provides for communication via a message set. The kit may be used with any aircraft that provides a rack or pylon for mounting the store and the capability to release the store. The kit may be used with aircraft having no existing capability to communicate with smart stores, with aircraft having an incompatible interface for modern stores or even with aircraft that have a compatible hardware interface for which the software is outdated. | 06-14-2012 |
20120150366 | Method And Device For The Passivation Of Guidance Orders Of An Aircraft - The device ( | 06-14-2012 |
20120150367 | Method And Device For Automatically Monitoring The Ability Of An Aircraft To Follow A Flight Trajectory With At Least One Turn - Method and device for automatically monitoring the ability of an aircraft to follow a flight trajectory with at least one turn. | 06-14-2012 |
20120158215 | Programmable Surface - In exemplary embodiments of this invention, a programmable surface comprises an array of cells. Each of the cells can communicate electronically with adjacent cells in the array, can compute, and can generate either normal thrust or shear thrust. Distributed computing is employed. The programmable surface may cover all or part of the exterior of a craft, such as an aircraft or marine vessel. Or, instead, the programmable surface may comprise the craft itself, which may, for example, take the form of a “flying carpet” or “flying sphere”. The thrust generated by the programmable surface can be employed directly to provide lift. Or it can be used to control the orientation of the craft, by varying the relative amount of thrust outputted by the respective cells. The number of cells employed may be changed on a mission-by-mission basis, to achieve “span on demand”. Each cell may carry its own payload. | 06-21-2012 |
20120158216 | APPARATUS AND METHOD FOR AUTOMATICALLY GENERATING SATELLITE OPERATION PROCEDURE PARAMETERS - An apparatus for automatically generating satellite operation procedure (SOP) parameters is provided. The apparatus includes a parameter extraction unit configured to extract one or more SOP parameters corresponding to an SOP; a transformation formula extraction unit configured to extract a transformation formula corresponding to the extracted SOP parameters; and a calculation unit configured to calculate values of the extracted SOP parameters based on property information for performing a satellite task and the extracted transformation formula. | 06-21-2012 |
20120158217 | DISTRIBUTED ACTIVE VIBRATION CONTROL SYSTEMS AND ROTARY WING AIRCRAFT WITH SUPPRESSED VIBRATIONS - A method and system is disclosed for controlling problematic vibrations in an aircraft having. The method and system have the ability to cancel problematic rotary wing helicopter vibrations using independent active force generator power and with distributed communications therebetween. | 06-21-2012 |
20120158218 | STEERING ANGLE CONTROL SYSTEM FOR AIRCRAFT - To provide an aircraft steering angle control system that minimizes the amount of skidding of an airframe that is turning on a low-μ taxiway surface such as an icy taxiway surface and allows for directional control of the airframe by a steering command, an aircraft steering angle control system that outputs an operation signal related to a steering angle as a control command signal for a nose steering wheel incorporates a nose wheel envelope protection including a reference steering angle setting unit that calculates a reference steering angle on the assumption that the airframe is not skidding; a skid detection unit that detects a skidding state of the airframe based on the reference steering angle; and a switch unit that selects a control command signal for a nose wheel in conjunction with the skid detection unit. | 06-21-2012 |
20120173052 | Method And Device For Automatically Monitoring Air Operations Requiring Navigation And Guidance Performance - The monitoring device ( | 07-05-2012 |
20120179307 | APPARATUSES AND METHODS FOR DISPLAYING AND RECEIVING TACTICAL AND STRATEGIC FLIGHT GUIDANCE INFORMATION - Methods and apparatuses for displaying and receiving tactical and strategic flight guidance information are disclosed. A method in accordance with one aspect of the invention includes displaying at least one first indicator to an operator of the aircraft, with a first indicator corresponding to a first instruction input by the operator for directing a first aircraft behavior and implemented upon receiving an activation instruction from the operator. At least one second indicator corresponding to a second instruction for directing a second aircraft behavior at least proximately the same as the first aircraft behavior is displayed, with the at least one second instruction to be automatically implemented at a future time. The at least one second indicator is at least approximately the same as the at least one first indicator. Indicators can be hierarchically organized to simplify presentation and reduce pilot training time. | 07-12-2012 |
20120185116 | INTEGRATED BLEED AND ENGINE CONTROLLER - An integrated electronic engine control and environmental control system bleed control apparatus for use with an aircraft engine. The apparatus comprises an electronic engine controller, an environmental control system bleed controller for controlling a flow of bleed air from the aircraft engine to an environmental control system located in an aircraft fuselage, and a housing for mounting on or near the aircraft engine. The housing contains both the electronic engine controller and the environmental control system bleed controller. | 07-19-2012 |
20120191273 | AIRCRAFT FLIGHT DATA DELIVERY AND MANAGEMENT SYSTEM WITH EMERGENCY MODE - An automated aircraft flight data and delivery management system and method operates in a normal state and a demand state. The demand state may be self-initiated or manually-initiated, and may be triggered during situations which include but are not limited to situations when the aircraft is in a potential or confirmed emergency situation. Data transmission increases in intensity when the system is in a demand state. | 07-26-2012 |
20120203401 | Onboard Maintenance System Network Optimization - An aircraft communication system includes an aircraft component, an Integrated Modular Avionics (IMA) unit, an Onboard Maintenance System (OMS), and a switch. The switch routes data provided by the aircraft component via a first communications protocol to the IMA unit, and mirrors the routed data to the OMS via a second communications protocol. The OMS processes and stores the received data, part of the received data, or the results of said processing. | 08-09-2012 |
20120209455 | Autopilot with Adaptive Rate/Acceleration Based Damping - A control system includes a rate-damping loop that uses a motion parameter error (heading pitch, heading yaw, attitude pitch, attitude yaw, and attitude roll) to non-linearly scale a rate-feedback signal so that at lower motion parameter error values, an acceleration feedback term plays a greater role in pitch compensation, while at greater motion parameter error values, a rate-feedback term plays a greater role in the pitch compensation. In some embodiments, a control system and method of controlling a motion parameter of a moving body are provided. A signal representing a motion parameter error is non-linearly combined with a signal representing a rate-of-change of a motion parameter (or body angle) to generate a non-linear rate-damping signal. The non-linear rate-damping signal is subtracted from the signal representing the motion parameter error to generate a signal to control one or more elements of the moving body. | 08-16-2012 |
20120209456 | Parallel Hybrid-Electric Propulsion Systems for Unmanned Aircraft - An unmanned air vehicle is provided, which includes an airframe and a parallel hybrid-electric propulsion system mounted on the airframe. The parallel hybrid-electric propulsion system includes an internal combustion engine and an electric motor. A hybrid controller is configured to control both the internal combustion engine and the electric motor. A propeller is connected to a mechanical link. The mechanical link couples the internal combustion engine and the electric motor to the propeller to drive the propeller. An alternate unmanned air vehicle includes a second propeller driven by the electric motor. In this alternate unmanned air vehicle, the internal combustion engine is decoupled from the electric motor. | 08-16-2012 |
20120215385 | AIRCRAFT SYSTEMS AND METHODS FOR PROVIDING EXHAUST WARNINGS - Aircraft system and method are provided for a first aircraft in an airport environment, the airport environment including a second aircraft. The system includes a sensor on the first aircraft configured to determine a temperature profile of engine exhaust from the second aircraft; and a processing unit coupled to the sensor and configured to construct a velocity profile of the engine exhaust from the second aircraft based on the temperature profile and to generate a warning for a pilot of the first aircraft based on the velocity profile. | 08-23-2012 |
20120215386 | Method And Device For Aiding The Flight Management Of An Aircraft - Method and device for aiding the flight management of an aircraft.
| 08-23-2012 |
20120215387 | TECHNIQUE FOR PROVIDING MULTIPLE UNDO AND REDO OPERATIONS FOR FLIGHT MANAGEMENT SYSTEMS - A technique for providing multiple undo and redo operations for flight management systems is disclosed. In one embodiment, in a method of providing multiple undo and redo operations for a flight plan in a flight management system, a temporary flight plan and a reference flight plan are created upon initiating a first revision on a created or default active flight plan. The temporary flight plan includes a copy of the active flight plan and the initiated first revision. The reference flight plan is a copy of the active flight plan. Further, multiple undo and redo functions are enabled upon initiating multiple revisions on the temporary flight plan for performing multiple undo and redo operations on the temporary flight plan. | 08-23-2012 |
20120221179 | UNMANNED AERIAL VEHICLE AND METHOD FOR ADJUSTING FLIGHT DIRECTION OF THE SAME - A method for adjusting a flight direction of an unmanned aerial vehicle (UAV) using a control device receives a first direction of the control device and a control command of the UAV, obtains a second direction of the UAV, and calculates an angle deviation between the first direction and the second direction. The method further adjusts the control command of the UAV according to the angle deviation to obtain an adjusted control command, and controls a flight direction of the UAV according to the adjusted control command | 08-30-2012 |
20120221180 | UNMANNED AERIAL VEHICLE AND CONTROL METHOD THEREOF - A method for controlling an unmanned aerial vehicle (UAV) using a control device receives a first direction of the control device and a control command of the UAV, obtains a second direction of the UAV, and calculates an angle deviation between the first direction and the second direction. The method further adjusts the second direction of the UAV according to the angle deviation, and controls a flight direction of the UAV according to the received control command. | 08-30-2012 |
20120232721 | DUAL-AIRCRAFT ATMOSPHERIC PLATFORM - A platform including two winged aircraft are tethered during flight by a single tether near their respective centers of gravity. The tether is windable about a reel, so that a distance between the aircraft can be changed during flight. The aircraft contain avionics configured to enable autonomous flight using natural wind gradients. One aircraft imposes aerodynamic forces on the other, through the tether, while flying at an altitude where wind speed is significantly different than wind speed at an altitude of the other aircraft. The two aircraft cruise back and forth within a maximum distance from a station on the ground. Cruise conditions are established using an iterative computer algorithm which utilizes flight measurements. The aircraft communicate information between each other, and the ground, and contain a payload which performs a useful function at high altitudes. | 09-13-2012 |
20120232722 | Automatic Configuration Control of a Device - Methods, systems, and devices for determining system/device configuration and setting a mode of operation based on the determined configuration. An air vehicle processor: (a) receives a component information | 09-13-2012 |
20120239227 | Variable Maximum Commandable Roll Rate for Directional Control During Engine-Out Rolling Maneuver - A system and a method for varying a maximum roll rate command for ensuring sufficient directional control during an engine-out rolling maneuver of a multi-engine aircraft. For a multi-engine airplane with a roll rate command flight control system, the primary flight control computer is used to vary the maximum commandable roll rate to preserve the desired control margins during roll maneuvers where the rudder is fully deflected to control a thrust asymmetry. When the engine-out yawing moment exceeds a specified value, the system sets a reduced limit on the amount of roll rate the pilot can command. | 09-20-2012 |
20120239228 | APPARATUS AND METHOD FOR CONTROLLING POWER GENERATION SYSTEM - A vehicle includes at least one propulsion member and a power generation system. The power generation system includes a power source and a transmission configured to provide torque to the at least one propulsion member. The power generation system further includes a control apparatus comprising an input device and a processor. The processor is configured to receive signals indicative of a power output command, a plurality of detected ambient air conditions, and a plurality of detected power generation system parameters. The processor is also configured to determine a plurality of power generation system control settings for improving efficiency of the vehicle based on at least one of signals indicative of the power output command, the signals indicative of the plurality of detected ambient air conditions, and the signals indicative of a plurality of power generation system parameters. | 09-20-2012 |
20120245767 | SYSTEM AND METHOD FOR EVALUATING OPERATION OF A VEHICLE WITH RESPECT TO A PLURALITY OF ENVIRONMENTAL FACTORS - A system installed with a vehicle for evaluating operation of the vehicle with respect to environmental factors includes: (a) operational sensors for sensing data relating to operational factors of the environmental factors; (b) an operational information store coupled with selected sensors for storing operational data received from the selected sensors relating to the operational factors; (c) an operational standards store for storing operational standards associated with operating the vehicle; (d) an operational standard compliance evaluation unit coupled with the information store and coupled with the standards store for effecting comparison of the operational data with the operational standards to ascertain an operational comparison result, and determining whether the vehicle complies with the standards based upon the comparison result; and (e) an operational report and store unit coupled with the compliance evaluation unit for receiving the operational determination and generating at least one report relating to the operational determination. | 09-27-2012 |
20120245768 | DEVICE AND METHOD FOR EVALUATION OF THE OPERATIONAL CAPABILITIES OF AN AIRCRAFT - A device for evaluation of the operational capabilities of an aircraft for informing a user about the capabilities of the aircraft to carry out a mission. Included are means for detecting malfunctions of aircraft equipment adapted for functioning during a mission. An evaluation device includes means for acquisition of information about the mission; a means for calculating observed feasibility level of the mission on the basis of at least one detected malfunction and the information obtained about the mission of the aircraft; and a means for presenting a synthetic reactive indicator, representative of the observed feasibility level of the mission in at least one instant of the mission. The means for acquisition, calculation and presentation are adapted for functioning during the mission, to inform the user about the observed feasibility level of the mission depending on the detection of new malfunctions and/or the modifications of the mission in course. | 09-27-2012 |
20120253555 | METHODS AND SYSTEMS FOR TRANSLATING AN EMERGENCY SYSTEM ALERT SIGNAL TO AN AUTOMATED FLIGHT SYSTEM MANEUVER - Systems, methods and apparatus are provided for translating an alert signal into an auto flight system (AFS) maneuver. The system comprises a first module. The first module is configured to receive an alert signal and to construct one or more AFS mode commands associated with the alert signal. The system also comprises a second module. The second module is configured to read and to execute the one or more AFS mode commands that when executed manipulate two or more standard AFS modes that implement the AFS maneuver. The system further comprises a state machine, which couples the first module to the second module and is configured to coordinate the construction of the one or more AFS mode commands by the first module with an execution of the one or more AFS mode commands by the second module. | 10-04-2012 |
20120253556 | REDUNDANT TWO STAGE ELECTRO-HYDRAULIC SERVO ACTUATOR CONTROL - A flight control system includes a dual stage actuator for moving a control surface. Each stage includes several control valves that are controlled independently to provide a desired redundancy. A flight controller generates a position command that is indicative of the position desired for the control surface. A first communication link is provided between several flight controllers to share information. Each of the flight controllers forwards the position command to actuator remote processing unit. The actuator remote processing unit receives position commands and generates a command signal that controls movement of the actuator using the control valves. Each of the actuator remote processing units is linked through a second communication link. Feedback and balancing of the different control valves is provided by the visibility accorded each actuator remote processing unit by the second communication link. | 10-04-2012 |
20120253557 | SYSTEMS AND METHODS FOR CONTROLLING THE SPEED OF AN AIRCRAFT - A system is provided for controlling the speed of an aircraft with a speed brake during flight. The system includes a guidance system configured to determine a target speed for the aircraft; a speed brake control system coupled to the guidance system and configured to compare the target speed to a current speed to generate speed brake guidance; and a display unit coupled to the speed brake control system and configured to display a visual representation of the speed brake guidance to a pilot of the aircraft. | 10-04-2012 |
20120253558 | Flight Control Laws for Constant Vector Flat Turns - An aircraft and method to control flat yawing turns of the aircraft while maintaining a constant vector across a ground surface. The aircraft includes a control system in data communication with control actuators, a lateral control architecture, a longitudinal control architecture, and an initialization command logic. The lateral control architecture controls the aircraft in the lateral direction, while the longitudinal control architecture controls the aircraft in the longitudinal direction. The initialization command logic automatically activates the lateral control architecture and the longitudinal control architecture to maintain a constant vector across the ground whenever a directional control input is made at low speed. | 10-04-2012 |
20120253559 | Method And Device For Automatically Detecting Erroneous Air Data On An Aircraft - The device ( | 10-04-2012 |
20120253560 | METHOD AND A DEVICE FOR ASSISTING THE PILOTING OF AN AIRCRAFT, AND AN AIRCRAFT - A method of assisting the piloting of an aircraft ( | 10-04-2012 |
20120253561 | RESPONSE MODE FOR CONTROL SYSTEM OF PILOTED CRAFT - Frequency multiplexed command signaling that permits a single pilot command interface (e.g. control stick) to serve as a multiple response mode interface for piloting a craft conforms with natural interface operation of most pilots. Highly augmented modes receive lower frequency components of the command signaling, and less augmented modes receive higher frequency components. This avoids the requirement for pilots to switch response modes. An embodying control system can be produced by miming feedback control loops encoding the respective response modes in parallel, and multiplexing the command signaling to each response mode, filtering each copy of the command signaling respectively according the respective feedback control loop, and then combining the output of each feedback control loop to compute actuation demand. | 10-04-2012 |
20120259483 | ACTUATION CONTROL SYSTEM - A dual redundant actuation control system for controlling a plurality of actuators for positioning a plurality of moveable aircraft components. The actuation control system includes a component controller. The component controller includes two component control channels. Each of the plurality of actuators is electrically connected to each of the two component control channels such that either of the two component control channels may control any or all of the plurality of actuators. | 10-11-2012 |
20120259484 | INFLATABLE PERSONAL RESTRAINT SYSTEMS - An electronic module assembly (EMA) for use in controlling one or more personal restraint systems. A programmed processor within the EMA is configured to determine when a personal restraint system associated with each seat in a vehicle should be deployed. In addition, the programmed processor is configured to perform a diagnostic self-test to determine if the EMA and the personal restraint systems are operational. In one embodiment, results of the diagnostic self-test routine are displayed on a display included on the electronic module assembly. In an alternative embodiment, the results of the diagnostic self-test routine are transmitted via a wireless transceiver to a remote device. The remote device can include a wireless interrogator or can be a remote computer system such as a cabin management computer system. | 10-11-2012 |
20120259485 | EMERGENCY COMMUNICATIONS CHANNEL SYSTEMS AND METHODS FOR SATELLITE COMMAND - Systems and methods for commanding a satellite are provided. A system for commanding a satellite includes a data bus and a payload coupled to the data bus, the payload including a payload receiver. The system further includes a primary receiver coupled to the data bus and a processor coupled to the data bus. The processor configured to receive a first command from the primary receiver via the data bus, and to receive telemetry data from the payload via the data bus. The processor is further configured to detect a second command by processing the telemetry data received from the payload, and to execute the detected second command. | 10-11-2012 |
20120265372 | AVIONICS DATA ENTRY DEVICES - Methods, systems, and apparatuses for the use of a wireless portable avionics device in conjunction with on-board flight systems and/or off-board service providers. The device may be used by aircraft personnel such as pilots and may act as a command/data entry and/or display tool to augment cockpit display systems. The device can receive flight data (e.g., a flight plan) from an off-board provider and automatically transfer it, as well as any previously prepared commands or data, to a flight management system and/or cockpit display systems. Commands and/or data (including pre-existing ones and ones entered in real-time) can be wirelessly transferred to the on-board flight systems which are not in direct physical contact with the device. Thus, the device can be easily manipulated during turbulence or under poor readability conditions. The device can be used to manipulate items shown on cockpit display systems in a timely and accurate manner. | 10-18-2012 |
20120271490 | METHOD FOR DISTRIBUTING BRAKING TORQUE BETWEEN BRAKED WHEELS FITTED TO AT LEAST ONE UNDERCARRIAGE OF AN AIRCRAFT - A method for distributing braking energy between a group of braked wheels 1 . . . p and fitted to N undercarriages of an aircraft, each of the braked wheels comprising a brake furnished with a stack of discs to which a load is selectively applied so as to generate a torque for braking the wheel. Each brake is equipped with means for measuring a thickness of the stack of discs, and in which:
| 10-25-2012 |
20120271491 | CAPTURING ENVIRONMENTAL INFORMATION - In general, a method performed on a vehicle includes determining that the vehicle is located within a predetermined range of a beacon, the beacon being associated with a beacon identification, navigating the vehicle to a first location based on determining that the vehicle is located with the predetermined range, generating a first report based on determining that the vehicle is located at the first location, the generating including: specifying the beacon identification, recording navigation data that includes an altitude, a distance from the beacon, and a bearing relative to the beacon, and recording environmental data. The method further includes transmitting the first report from the vehicle to a base station, the first report including the beacon identification, the navigation data, and the environmental data. | 10-25-2012 |
20120283897 | Aircraft Task Management System - A method and apparatus for managing tasks in an aircraft. A current state of the aircraft is identified. A group of tasks is identified using a task database and the current state of the aircraft. The task database comprises the tasks for performance during different phases of flight of the aircraft by a flight crew and the group of tasks comprises different types of tasks from the tasks. The group of tasks is presented in a computer system. | 11-08-2012 |
20120290153 | FLIGHT CONTROL SYSTEM WITH ALTERNATE CONTROL PATH - A flight control system and method including a primary flight control path between one or more pilot controls and control surface actuators on an associated aircraft, wherein the primary control path includes one or more flight control computers and one or more first data concentrators; and a secondary flight control path between the one or more pilot controls and the control surface actuators, wherein the secondary flight control path utilizes direct mode control laws to control the control surface actuators; wherein the primary flight control path and the secondary flight control path are independent from each other and the secondary flight control path is operative upon detection of a fault in the primary flight control path. | 11-15-2012 |
20120290154 | PROVIDING DATA FOR PREDICTING AIRCRAFT TRAJECTORY - The present invention provides a system and method of producing a description of the flight intent of an aircraft expressed using a formal language. The description may be used to generate a predicted aircraft trajectory, for example by air traffic management. Rules are used in association with information provided to express the flight intent of the aircraft in a formal language. The flight intent describes a flight in terms of flight segments, and provides information of the path to be flown and how it is to be flown. The flight intent does not necessarily define unambiguously the aerodynamic configuration of the aircraft and the motion of the aircraft during the flight. The flight intent is used alongside other information to generate the aircraft intent that does describe unambiguously the aircraft's trajectory. | 11-15-2012 |
20120296496 | UPGRADED FLIGHT MANAGEMENT SYSTEM AND METHOD OF PROVIDING THE SAME - A preexisting FMS system may be upgraded to increase its functionality while still taking advantage of certain components of the legacy system previously provided on the aircraft and replacing other preexisting components with different components for enhancing the functionality of the FMS system. The preexisting IRU, CADC, DME receiver and DFGC in the upgraded FMS system are in communication with the legacy AFMC but, instead of employing the legacy EFIS which existed in the preexisting FMS system, the EFIS is replaced by a data concentrator unit as well as the display control panel and integrated flat panel display, and a GPS receiver. The upgraded FMS system is capable of such increased functionality as increased navigation database storage capacity, RNP, VNAV and RNAV capability utilizing a GPS based navigation solution, and RTA capability, while still enabling the legacy AFMC to exploit its aircraft performance capabilities throughout the flight. | 11-22-2012 |
20120296497 | UNMANNED AERIAL VEHICLE AND METHOD FOR CONTROLLING THE UNMANNED AERIAL VEHICLE - In a method for controlling an unmanned aerial vehicle (UAV), a digital image is obtained by an image capturing device of the UAV. The method detects an object in the digital image, determines a distance between the detected object and the UAV, and obtains a flight direction of the UAV if the distance is less than a preset value. The method further calculates a relative position and a relative angle between the detected object and the UAV, determines a flight limiting range of the UAV according to the relative position and the relative angle, and controls the flight direction of the UAV according to the flight limiting range. | 11-22-2012 |
20120296498 | METHOD FOR CONTROLLING THE DECELERATION ON THE GROUND OF A VEHICLE - The invention relates to a method for controlling the deceleration on the ground of a vehicle. The method obtains, from the crew of the vehicle or from an outside operator, parameters relating to its current position and its current speed. Then it determines a reference position and speed of the vehicle, the reference position being a theoretical position to be reached by the vehicle. Finally it determines, from indicated parameters and from reference parameters, a deceleration command with a view to ending up at a target position at a preselected speed. | 11-22-2012 |
20120296499 | DEVICE AND A METHOD FOR CONSTRUCTING A FLIGHT PATH IN ORDER TO REACH A DESTINATION | 11-22-2012 |
20120303183 | NETWORK, IN PARTICULAR FOR AN AIRCRAFT AND SPACECRAFT, METHOD AND AIRCRAFT AND SPACECRAFT - The present invention provides a network, in particular for an aircraft and spacecraft, comprising a network line and at least two network access devices which are interconnected by the network line and between which data of different levels of priority can be transmitted, the network access devices being formed so as allocate data with a level of priority allocated to the respective data, at least two different levels of priority being provided for the data depending on the relevance of the respective data, and the data being transmitted on the network line in fixed time slots depending on the level of priority assigned in each case. The present invention further provides a method and an aircraft and spacecraft. | 11-29-2012 |
20120310448 | AIRCRAFT ENVIRONMENTAL THREAT DETECTION AND MITIGATION - A method of aircraft engine thermal threat mitigation includes detecting an airflow thermal profile at a location on the aircraft forward of an aircraft engine inlet and transmitting the thermal profile to an aircraft control system. The thermal profile is compared to a catalog of thermal threat profiles at the aircraft control system and a determination is made if a thermal threat is present based on the comparison. A thermal threat mitigation measure is initiated to reduce an effect of the thermal threat on aircraft engine performance. | 12-06-2012 |
20120310449 | STRUCTURAL HEALTH MANAGEMENT WITH ACTIVE CONTROL USING INTEGRATED ELASTICITY MEASUREMENT - A system and method for actively controlling a structure is disclosed. At least one non-optimal event is identified in real-time based on at least one real-time elasticity measurement, if an event threshold exceeds a predetermined value. In response to an active control command, a control mechanism is then activated in real-time to compensate for the non-optimal event. | 12-06-2012 |
20120310450 | METHODS AND SYSTEMS FOR BRIEFING AIRCRAFT PROCEDURES - Methods and systems are provided for providing procedure information associated with an aircraft procedure onboard an aircraft. An exemplary method involves obtaining a briefing sequence for the aircraft procedure and providing the procedure information via the output device, wherein the procedure information is provided in accordance with the briefing sequence. When the output device is realized as an audio output device, the procedure information is sequentially provided auditorily via the audio output device. In one or more embodiments, the procedure information is sequentially indicated on a display device onboard the aircraft in concert with the auditorily provided procedure information. | 12-06-2012 |
20120310451 | METHOD AND DEVICE FOR MEASURING THE ANGULAR VELOCITY OF A LUMINANCE TRANSITION ZONE AND STEERING AID SYSTEM FOR FIXATION AND TRACKING A TARGET COMPRISING AT LEAST ONE SUCH LUMINANCE TRANSITION ZONE - The present invention relates to a method for measuring a time delay between two output signals measured by two adjacent optical sensors, the time delay resulting from a movement of an object moving in a given direction. The method comprises the steps:
| 12-06-2012 |
20120323409 | Dynamically Reconfigurable Electrical Interface - A dynamically reconfigurable electrical interface is disclosed that can be used in various applications, including avionics communications. In one embodiment, a first switch receives an input signal and routes it to the applicable signal conditioning path unit that conditions the input signal, after which a second switch routes it to an amplifier. The amplifier provides an amplified signal to an analog-to-digital converter that generates a corresponding numerical value based on the voltage of the amplified signal that is analyzed by a processor to determine information conveyed by the input signal based on a particular electrical interface. Multiple distinct interfaces can be accommodated by on one more processors accessing instructions sets for processing information corresponding to a particular electrical interface. In another embodiment, the processor provides numerical values to a digital-to-analog converter producing an analog signal that is amplified, routed, and conditioned to convey information using a particular electrical interface. | 12-20-2012 |
20120323410 | FATIGUE MANAGEMENT SYSTEM - A fatigue management system for determining the individual life of an aircraft, particularly the individual life of components of a helicopter, by means of an on board virtual load sensor and a method of operating a fatigue management system. | 12-20-2012 |
20120330482 | METHOD OF CONTROLLING THE STEERING OF A STEERABLE PORTION OF AN AIRCRAFT UNDERCARRIAGE - The invention relates to a method of controlling the steering of a steerable portion of an aircraft undercarriage that is fitted both with a steering member for steering the steerable portion and also with at least two angular position sensors for sensing the angular position of the steerable portion in order to deliver respective signals representative of the angular position of the steerable portion, wherein the steering member is controlled by means of servo-control using information that is representative of the angular position of the steerable portion. According to the invention, the information representative of the angular position that is used is a mean of the angular positions sensed by the at least two angular position sensors. | 12-27-2012 |
20130006447 | METHOD FOR MANAGING A BRAKING SYSTEM FOR AN AIRCRAFT FITTED WITH ELECTROMECHANICAL BRAKES - A braking system for an aircraft with electric brakes comprising plural electromechanical actuators ( | 01-03-2013 |
20130013131 | METHOD AND APPARATUS FOR PARAFOIL GUIDANCE THAT ACCOUNTS FOR GROUND WINDS - A method is described that involves determining a higher altitude wind. The method further includes determining a wind model with the higher altitude wind. The wind model includes a linear or logarithmic increase in wind magnitude with increasing altitude beneath the higher altitude. The method further includes determining locations of a flight path for a parafoil based on calculations that use the wind model. The calculations are performed by an electronic control unit that is transported by the parafoil. The method also includes controlling the parafoil's flight path consistently with the determined locations. The controlling is performed by the control unit. | 01-10-2013 |
20130013132 | AUTOMATIC PARAFOIL TURN CALCULATION METHOD AND APPARATUS - A method is described that involves performing the following with a parafoil's control unit composed of electronic circuitry while the control unit is being transported with a parafoil: determining a desired exit of a turn; determining a desired time for the turn; determining the parafoil's actual entrance for the turn; determining an arc between the actual entrance and the desired exit; and, incorporating said arc as said parafoil's planned flight trajectory through said turn. | 01-10-2013 |
20130018532 | SOLAR ENERGY COLLECTION FLIGHT PATH MANAGEMENT SYSTEM FOR AIRCRAFTAANM Segal; Matthew JonathanAACI CalabasasAAST CAAACO USAAGP Segal; Matthew Jonathan Calabasas CA USAANM Wise; Kevin AndrewAACI St. CharlesAAST MOAACO USAAGP Wise; Kevin Andrew St. Charles MO US - A method and apparatus for managing solar power collection. A position of the sun is identified relative to an aerospace vehicle while the aerospace vehicle is moving along a flight path. A level of power generation is identified by a solar power generation system while the aerospace vehicle moves along the flight path using a threat management module and equivalent radar signature data. The threat management module uses the equivalent radar signature data to identify the level of power generation by the aerospace vehicle from different positions of the sun relative to the aerospace vehicle, and the equivalent radar signature data is based on solar power generation signature data identifying the level of power generation for the different positions of the sun relative to the aerospace vehicle. A change in the flight path that results in a desired level of power generation is identified by the solar power generation system. | 01-17-2013 |
20130024050 | ON-BOARD MAINTENANCE SYSTEM OF AN AIRCRAFT, AND ASSOCIATED AIRCRAFT - An on-board maintenance system for an aircraft, said aircraft comprising pieces of equipment connected together through a first on-board data transmission network for exchanging operational data intended for piloting the aircraft, said maintenance system including a processing unit and being characterized in that it comprises a second data transmission network, distinct from the first network, for exchanging data intended for maintenance of the equipment of the aircraft, said second network connecting at least some of said pieces of equipment to the processing unit; said processing unit are being adapted for receiving in real time, a data provided by the pieces of equipment on the second network and processing them with view to determining the cause of equipment malfunctions according to at least said received data. | 01-24-2013 |
20130024051 | DEVICE AND METHOD FOR REGULATING THE HUMIDITY OF A FUEL CELL - A device and a method for controlling the air humidity in a fuel cell detect a step response in the output voltage of a fuel cell when the supply to electrical loads is interrupted, and determine parameters of the dynamic time characteristic from the detected step response, and thus calculate a capacitance of the fuel cell. As a function of any deviation from a predetermined capacitance, a humidity control unit is caused to increase or decrease the humidity. This makes in situ detection of the humidity balance of a fuel cell possible, and this can keep the electrical power thereof constant for a relatively long period, and this can increase the intervals between maintenance. | 01-24-2013 |
20130030610 | Automatic Estimation Process And Device For A Flight Parameter Vector In An Aircraft, As Well As Detection Methods And Assemblies For A Failure Affecting Such A Vector - Automatic estimation process and device for a flight parameter vector in an aircraft, as well as detection methods and assemblies for a failure affecting such a vector. | 01-31-2013 |
20130035807 | BIT TRANSMISSION VERIFICATION IN AN ARINC-BASED SYSTEM - An example data verification method includes communicating a bit from a transmitter module to a receiver module through a bus. The bit forms a portion of an ARINC word. The method verifies the bit at the bus using the transmitter module. An example data communication assembly includes a receiver module, and a data communication bus that communicates a bit to the receiver module. The bit forms a portion of an ARINC word. A transmitter module communicates the bit to the data communication bus. The transmitter module monitors communication of the bit from the data communication bus to the receiver module. | 02-07-2013 |
20130035808 | AIRCRAFT WITH A CONTROL DEVICE - An aircraft with aerofoils including a main wing and a control flap that includes an adjustment flap. The aircraft includes an actuator for the control flap, as well as a sensor device for acquiring the position of the control flap, an arrangement of flow-influencing devices for influencing the fluid that flows over a segment of the main wing, and flow-state sensor devices for measuring the flow state. The aircraft includes a flight control device connected to the sensor device for acquiring the position of the control flap and to the flow-state sensor devices, and connected to the actuator and flow-influencing devices for transmitting actuating commands, and a flight-state sensor device connected to the flight control device for transmitting flight states. The flight control device includes a function that selects the flow-influencing devices that are operated for optimising local lift coefficients on the aerofoil, depending on the flight state. | 02-07-2013 |
20130041527 | VARIABLE BANDWIDTH CONTROL ACTUATION METHODS AND APPARATUS - Some embodiments relate to a method of controlling a flight of a flight vehicle according to a first mode of operation and changing the mode of operation to a second mode of operation having a different bandwidth than the first mode of operation. Other embodiments relate to a flight-control system for a flight vehicle configured to control a flight of a flight vehicle according to a first mode of operation and to control the flight of the flight vehicle according to a second mode of operation to use less energy than the first mode of operation. Other embodiments relate to a control actuation system configured to control positions of aerodynamic elements in a flight vehicle in response to commands from a guidance system according to a first mode of operation and to change the mode of operation to a second mode of operation having a different bandwidth than the first mode of operation. | 02-14-2013 |
20130041528 | Intelligent modular aerospace system - An Intelligent Modular Aerospace System (IMAS) is a paradigm shift in the architecture, utility, efficiency, operation, test/checkout, qualification testing and adaptability of an aerospace application system that provides Time/Space/Position Information, Data Acquisition/Processing/Relay, Power Generation/Distribution, avionic solutions, navigation, and command/data handling. IMAS ( | 02-14-2013 |
20130046422 | ONBOARD FLIGHT PLANNING SYSTEM - According to the application, a method for generating a flight route of an aircraft by an aircraft based computer system is disclosed. The method comprises the execution the following steps, which are executed by the aircraft based computer system. A mission specific data subset is received from a ground system. It is checked whether there are predefined routes from a departure airport to a destination airport. If it is determined that predefined route are available which are in accordance with over-flight permissions the predefined routes are used as a set of candidate routes for deriving a flight route. Otherwise, a set of proposed flight routes is generated which comprises at least one proposed flight route. Over-flight permissions are checked for the set of proposed flight routes. The steps of generating a set of proposed flight routes and of checking the over-flight permissions are repeated until at least one proposed flight route is found to be in accordance with the over-flight permissions. The one or more flight routes or routes which are in accordance with the over-flight permissions are used as a set of candidate routes for deriving a flight route. A flight route is derived from the set of candidate routes. | 02-21-2013 |
20130054053 | TORQUE BASED POWER LIMIT CUEING SYSTEM AND METHOD - A torque based power limit cueing system is provided and includes an engine computer to compile data relating to torque and additional information of each of one or more engines, an active stick by which tactile cueing are provided to a pilot and by which the pilot inputs control commands, a multi-function display (MFD) by which visible cues are provided to the pilot and a flight control computer (FCC) operably coupled to the engine computer, the active stick and the multi-function display, the FCC being configured to receive the data from the engine computer and to output tactile cue commands and visible commands in accordance with the torque and the additional information of each of the one or more engines to the active stick and the MFD, respectively. | 02-28-2013 |
20130054054 | Helicopter Sling-Load Stability Control and Release System - A sling load computer-operated hook assembly for helicopter or unmanned aerial vehicle (UAV) use is provided. The hook assembly allows automated pick-up and delivery. The computer hook assembly also (1) directs navigation of the aircraft, (2) finds and engages loads for pickup, (3) controls stability of the sling load enroute, and (4) releases the load at the delivery point. The self-contained feature allows the hook assembly to be moved from aircraft to aircraft. The hook assembly senses weight, motion and position of the load for stability control. An integral GPS unit is used to direct navigation. These data are transmitted to the aircraft autopilot and flight director instruments to provide navigation to the designated points and to control load stability enroute. Mission data for pick-up and release points can be received remotely from a command and control tactical data net. Alternately, mission data can be locally entered. | 02-28-2013 |
20130054055 | METHOD AND SYSTEM FOR INTEGRATING ENGINE CONTROL AND FLIGHT CONTROL SYSTEM - A method and system of operating an aircraft system are provided. The aircraft system includes an integrated aircraft flight control system that includes an engine control system configured to generate engine performance and health information. The integrated aircraft flight control system also includes a flight control system configured to generate flight information and trajectory intent information. The integrated aircraft flight control system further includes a communications channel communicatively coupled between the engine control system and the flight control system, where the engine control system is configured to transmit the generated engine performance and health information to the flight control system using the communications channel and the flight control system is configured to transmit the generated flight information and trajectory intent information to the engine control system using the communications channel. | 02-28-2013 |
20130060404 | SYSTEMS AND METHODS FOR BRAKING SYSTEM TESTING - Systems and methods disclosed herein may be useful for testing braking systems for use in, for example, an aircraft. A system is disclosed that allows for built in testing. For example, a method if provided comprising sending, from a brake controller, a test command set to at least one of an electromechanical actuator (EMAC) and a brake servo valve (BSV) in response to a landing gear retraction, receiving, at the brake controller, feedback from the at least one of the EMAC and the BSV in response to the test command set, and comparing, at the brake controller, the feedback with a predetermined signature. | 03-07-2013 |
20130060405 | FLIGHT CONTROL SUPPORT DEVICE - Disclosed is a flight control support device which sets a flight restricted area W along a terrain, thereby achieving improvement in safety of a small aircraft A and sufficiently securing the degree of freedom of flight course selection of a pilot. The flight control support device includes a terrain information acquirer, an aircraft information acquirer, a flight restricted area setter which sets the flight restricted area W along the terrain on the basis of the terrain information acquired by the terrain information acquirer and the aircraft information acquired by the aircraft information acquirer, and a flight control supporter which supports flight control of a flying object on the basis of the flight restricted area set by the flight restricted area setter. | 03-07-2013 |
20130073123 | Energy Control Apparatus For Controlling Hybrid Energy Sources For An Aircraft - An energy control apparatus for controlling hybrid energy sources for an aircraft is designed for determining an operating characteristic of an energy source, a demand of at least one first consumer for a first resource and a demand of a second consumer for a second resource. The energy control apparatus activates the energy source in dependence on the demand for the first resource and the second resource and, if there is no demand for a first or second resource that is generatable by the energy source and is present in excess, supplies a third consumer with the excess resource. This makes it possible for an energy system to operate different consumers independently of the type of generated resources and their dependencies during the generation. | 03-21-2013 |
20130079955 | SENSOR SYSTEM - Concepts and technologies are disclosed herein for a sensor system for detecting, characterizing, monitoring, and analyzing data. According to some embodiments disclosed herein, a monitoring system is configured to obtain data from a sensor system. The sensor system includes two or more sensors and can indicate an operating state detected at a monitored structure by the sensors. The monitoring system also obtains operational data including a threshold value for the sensors and an expected value for the sensors. The monitoring system is configured to adjust the thresholds based, at least partially, upon the operational data to obtain an adjusted threshold value, and to compare the data value to the adjusted threshold. The monitoring system can determine if the monitored structure is operating in an alarm condition. | 03-28-2013 |
20130079956 | METHOD OF REGULATING THE PROPULSIVE SPEED OF A HYBRID HELICOPTER - A method of regulating the propulsion speed of a hybrid helicopter. In application of a correction process for protecting the hybrid helicopter, piloting orders generated by a manual control member relate to an airspeed setpoint and they are corrected by control means in accordance with at least one correction mode in which the piloting orders are corrected in application of a rule that takes account of a setpoint consumed power corresponding to the airspeed setpoint derived from the piloting order. | 03-28-2013 |
20130090786 | SYSTEMS AND METHODS FOR MANAGING CONTROLLER PILOT DATA LINK COMMUNICATION (CPDLC) SYSTEMS - Systems and methods for a non-integrated CPDLC solution are provided. In one embodiment, the system includes: a first and second computing system for respectively executing a first and second CPDLC application; a Human Machine Interface coupled to the first and second computing systems, the Human Machine Interface providing access to display screens generated by both the first and second CPDLC applications; and a data authority function that determines a data authority application from the first and second CPDLC applications based on which of the first and second CPDLC applications has a current data authority (CDA) session. The data authority function prevents the first CPDLC application from establishing a concurrent current data authority session when the second CPDLC application is the data authority application. The data authority function prevents the second CPDLC application from establishing a concurrent current data authority session when the first CPDLC application is the data authority application. | 04-11-2013 |
20130090787 | THREE-DIMENSIONAL DIGITAL MAP - Disclosed herein is a three-dimensional (3D) digital map system for implementing a navigation and ground collision preventing method using 3D terrain information. The 3D digital map system includes a terrain referenced navigation module configured to receive data from EGI (Embedded GPS/INS), a radio-altimeter (RALT) and a map database, corrects the data to perform accurate navigation computation, and outputs the corrected data, a collision avoidance warning module configured to generate a warning against collision of an aircraft with the ground or an obstacle using the corrected data, a 3D terrain database and an obstacle database, a terrain following module configured to generate a terrain following trajectory of the aircraft using the same information, and a Passive Ranging module configured to receive the 3D terrain database and line-of-sight (LOS) information of a target and calculate distance and position information of the target located on the ground. | 04-11-2013 |
20130110323 | METHODS AND SYSTEMS FOR AVOIDING A COLLISION BETWEEN AN AIRCRAFT ON A GROUND SURFACE AND AN OBSTACLE | 05-02-2013 |
20130110324 | Energy Protection Device For An Aircraft | 05-02-2013 |
20130110325 | CONTROL SYSTEM FOR UNMANNED AERIAL VEHICLE UTILIZING PARALLEL PROCESSING ARCHITECTURE | 05-02-2013 |
20130110326 | PARTICLE SENSOR FOR IN SITU ATMOSPHERIC MEASUREMENT | 05-02-2013 |
20130116862 | AUTOBRAKING INTERLOCK FOR AN AIRCRAFT ELECTRIC BRAKE SYSTEM - An electric autobrake interlock system for an aircraft includes an autobrake power interlock mechanism that prevents inadvertent (uncommanded) application of brakes. The autobrake power interlock removes operating power from the brake actuators whenever the autobrake actuation data does not indicate a legitimate autobrake application condition. The interlock processing occurs in parallel with the autobrake command processing such that even if an inadvertent autobrake command is generated, the brake actuators will be enable to act upon the inadvertent autobrake command. In this regard, the brake actuators are unable to apply brakes automatically unless the following two actions happen concurrently: the operating power is provided to enable the electric brake actuators and autobrake actuation control is commanded in response to the legitimate autobrake application condition. | 05-09-2013 |
20130124015 | MULTI CORE VEHICLE MANAGEMENT SYSTEM AND METHOD - A flight management system (FMS) including a plurality of FMS components that can include a civil FMS component and a tactical FMS component. Each FMS component can have a processor programmed to execute an FMS software product. The FMS can also include a multi core FMS manager configured to control a plurality of flight management systems and coupled to the plurality of FMS components. The multi core FMS manager can include a plurality of FMS managers, each coupled to one of the FMS components, and a platform interface manager coupled to an avionics system. Each FMS manager can be adapted to transmit flight management data to, and to receive flight management data from, the FMS component to which it is coupled. The platform interface manager can be adapted to provide each FMS component access to the avionics system, such that an aircraft operator can control each FMS component via the FMS. | 05-16-2013 |
20130124016 | Derived Rate Monitor for Detection of Degradation of Fuel Control Servo Valves - A system for detecting degradation of a servo valve; having a controller, a servo valve, a position sensor, and a rate monitor. The controller receives inputs and transmits command data. The servo valve has an actuator and is conductively coupled to the controller to receive command data from the controller and move the actuator in response to the command data. The position sensor operably associated with the servo valve for measuring movement of the actuator and transmits corresponding movement data to the controller. The rate monitor coupled to the controller and position sensor for receiving the command data and the movement data as inputs respectively. The rate monitor processes the inputs to produce a steady state rate error signal. The rate monitor compares the steady state rate error signal to selected operational limits and produces a telemetry output when the operational limits are exceeded. | 05-16-2013 |
20130124017 | Control Panel System for a Vehicle - A method and apparatus for managing a programmable control panel for a vehicle. A number of first level control functions is assigned to the programmable control panel for the vehicle. A number of second level control functions is assigned to the programmable control panel based on a health of programmable control panels in the vehicle. | 05-16-2013 |
20130124018 | METHOD AND APPARATUS FOR USING ELECTRONIC FLIGHT BAG (EFB) TO ENABLE FLIGHT OPERATIONS QUALITY ASSURANCE (FOQA) - A method for using an Electronic Flight Bag (EFB) located on an aircraft to communicate Flight Operations Quality Assurance (FOQA) data to a remote aircraft flight data collection unit, is disclosed. The method may include receiving FOQA data from one or more aircraft systems while the aircraft is in-flight, and automatically transmitting the received FOQA data to a remote aircraft flight data collection unit for analysis. | 05-16-2013 |
20130124019 | AIRCRAFT CONTROL APPARATUS AND AIRCRAFT CONTROL SYSTEM - A plurality of control channels each include a power supply, an interface that receives a manipulation signal, an arithmetic processing portion that calculates and generates an operation command signal for actuators based on the manipulation signal, and a signal determination unit that determines a control signal for finally controlling the operation of the actuators and outputs the control signal. The arithmetic processing portions respectively provided in the plurality of control channels have designs different from one another. Each of the signal determination units determines the control signal by receiving a first operation command signal generated by the arithmetic processing portion of the control channel in which that signal determination unit is provided, and a second operation command signal generated in the arithmetic processing portion of another of the control channels, and comparing the first operation command signal and the second operation command signal, and outputs the control signal. | 05-16-2013 |
20130124020 | AUTONOMOUS COLLISION AVOIDANCE SYSTEM FOR UNMANNED AERIAL VEHICLES - Autonomous collision avoidance systems for unmanned aerial vehicles are disclosed. Systems illustratively include a detect and track module, an inertial navigation system, and an auto avoidance module. The detect and track module senses a potential object of collision and generates a moving object track for the potential object of collision. The inertial navigation system provides information indicative of a position and a velocity of the unmanned aerial vehicle. The auto avoidance module receives the moving object track for the potential object of collision and the information indicative of the position and the velocity of the unmanned aerial vehicle. The auto avoidance module utilizes the information to generate a guidance maneuver that facilitates the unmanned aerial vehicle avoiding the potential object of collision. | 05-16-2013 |
20130131896 | METHOD OF ASSISTED PILOTING OF A ROTARY WING AIRCRAFT HAVING AT LEAST ONE PROPULSION PROPELLER, AN ASSISTED PILOTING DEVICE, AND AN AIRCRAFT | 05-23-2013 |
20130138268 | MULTI CORE VEHICLE MANAGEMENT MULTI CORE MANAGER SYSTEM AND METHOD - A computerized method for transmitting data between a multi core vehicle management system and a vehicle system. The method can include receiving, at a vehicle management system computer, a vehicle system request message from a requesting vehicle management system component. The requesting vehicle management system component can be one of a plurality of vehicle management system components, and the vehicle system request message can have a destination vehicle system component. The method can include generating a sanitized vehicle system request message based on the requesting vehicle management system component and the destination vehicle system component. The sanitized vehicle system request message can be transmitted to said destination vehicle system component. | 05-30-2013 |
20130138269 | MULTI CORE VEHICLE MANAGEMENT COUNTERMEASURES SYSTEM AND METHOD - A computerized method for performing countermeasure transmission of decoy vehicle data. The method can include receiving a vehicle management data message from one of a plurality of vehicle management system components. The vehicle management data message can have data indicating at least one destination component, and the at least one destination component can include a civil transponder. The method can include transforming said vehicle management data message into a decoy vehicle management data message and transmitting the decoy flight management data message to at least one of the at least one destination component(s). | 05-30-2013 |
20130138270 | FLIGHT CONTROL LAWS FOR AUTOMATIC HOVER HOLD - A system and method to control hovering flight of a rotary aircraft. The system including a lateral speed hold loop, a longitudinal loop, a vertical control loop, and a directional loop. The method includes defining a first flight envelope having a first groundspeed threshold; defining a second flight envelope having a second groundspeed threshold, the second flight envelope being defined within the first envelope; engaging a hover hold with a control law hover hold architecture as the aircraft enters the first flight envelope; and engaging a position hold with a control law position hold architecture as the aircraft enters the second flight envelope. | 05-30-2013 |
20130138271 | DISTRIBUTED AVIONICS - A distributed avionics system arranged in an aerial vehicle for controlling at least one avionics function. A plurality of avionics processing subsystems are interconnected in a network. Each avionics processing subsystem includes a processor arranged to process at least one task so as to provide a set of data messages including at least one unit of data related to controlling the at least one avionics function on basis of provided input data, related to conditions of the at least one avionics function. A memory module is in operative connection with the processor and is arranged to store instructions for the processor to process the at least one task. At least one of the avionics processing subsystems is arranged to transmit at least one synchronization cycle start signal onto the network | 05-30-2013 |
20130151039 | METHOD FOR OPTIMIZING THE OVERALL ENERGY EFFICIENCY OF AN AIRCRAFT, AND MAIN POWER PACKAGE FOR IMPLEMENTING SAME - A method and system limiting specific consumption of an aircraft by matching sizing of a power supply to actual power needs of a cabin pressure control system. The method optimizes overall efficiency of energy supplied onboard an aircraft including, in an environment near the cabin, at least one main power-generating engine, sized to serve as a single pneumatic energy-generating source for the cabin and as an at most partial propulsive, hydraulic, and/or electric energy-generating source for the rest of the aircraft. The method minimizes power differential between a nominal point of the power sources when the sources are operating, and a sizing point of non-propulsive energy contributions of the sources when the main engine has failed, by equally dividing power contributions of the main engines and the main power generator under nominal operating conditions and in an event of failure of a main engine. | 06-13-2013 |
20130158749 | METHODS, SYSTEMS, AND APPARATUSES FOR MEASURING FLUID VELOCITY - Methods, systems, and apparatuses are disclosed for a measuring the velocity of a fluid. | 06-20-2013 |
20130158750 | Energy Management On Board an Aircraft - Energy management on board an aircraft includes: a plurality of thermal and electrical energy sources, a plurality of loads which are capable of being supplied with power by the various energy sources, among which at least one load is capable of being supplied with power by an electrical energy source and by a thermal energy source, and real-time management means for energy transfers from the various energy sources to the various loads as a function of the present and future energy requirement of the various loads and the present and future availability of the various sources, with the management means providing a permanent and standardized correlation between thermal and electrical energies. | 06-20-2013 |
20130166110 | AIRCRAFT WITH AN ARRANGEMENT OF FLOW-INFLUENCING DEVICES - An aircraft, which has a respective arrangement of flow-influencing devices in at least one surface segment of each wing extending in the wingspan direction in order to influence the fluid flow over the surface segment, and of flow condition sensor devices for measuring the flow condition on the respective segment, and a flight control device, wherein the flight control device has a flow-influencing target parameter setting device connected with the arrangement of flow-influencing devices for generating target parameters for the flow-influencing devices of the at least one surface segment, wherein the flow-influencing devices are designed in such a way as to use the target parameters to change the local lift coefficients or correlations between the drag and lift coefficients in the segment where respectively located. | 06-27-2013 |
20130166111 | METHOD FOR CONTROLLING A HIGH-LIFT DEVICE OR A FLIGHT CONTROL SURFACE, SYSTEM AND AIRCRAFT OR SPACECRAFT - The present invention discloses a method for controlling a high-lift device or a flight control surface of an aircraft or spacecraft, especially with a system according to the present invention, comprising the steps of receiving, at at least one first control unit, a command signal from a commander unit via a data network, providing a primary control signal to at least one secondary control unit via the data network, wherein the primary control signal depends on the received command signal, receiving, at the at least one second control unit, a sensor signal of one or more sensors of the high-lift device or flight control surface, and providing a secondary control signal to one or more actuators of the high-lift device or flight control surface, wherein the secondary control signal depends on the received sensor signal. Furthermore, the present invention discloses a system and an aircraft or spacecraft. | 06-27-2013 |
20130166112 | Method and Device for Determining a Lateral Trajectory of an Aircraft and Associated Flight Management System - A method, and an associated device, is provided for the determination, by a flight management system of an aircraft, of a lateral trajectory of said aircraft on the basis of a predefined flight plan allowing consecutive conflicts to be resolved in an improved manner. This allows an improved lateral trajectory to be designed in the case where multiple trajectory conflicts exist. The trajectory obtained is closer to the flight plan defined by the pilot. The propagation of trajectory conflicts to the following flight segments is thus avoided. In fact, instead of propagating the trajectory conflict from one resolution to another, the method allows the conflict to be resolved in a space delimited at most by the input of the first conflict and the output of the last conflict. | 06-27-2013 |
20130173090 | Aircraft Flight Management Aid Device - A configured aircraft flight management aid system comprises: means of interpretation receiving data taken from external instructions from an external control center, data relating to aircraft equipment failures, cabin problems and problems related to the environment of the aircraft; means of determination receiving data from the means of interpretation and determining at least one reference constraint associated with at least one parameter representative of a flight path, a reference constraint associated with a reference parameter comprising a new constraint, different from the initial constraint when the item of data effectively necessitates following a new path, different from the initial path, and a reference constraint comprising the initial constraint when the means of determination do not have access to any data relating to an event effectively necessitating following a new path; warning means generating a warning to an operator when the path actually flown does not comply with said reference constraint. | 07-04-2013 |
20130179008 | USING PREDICTED MOVEMENT TO MAINTAIN OPTICAL-COMMUNICATION LOCK WITH NEARBY BALLOON - A balloon may include an optical-communication component, which may have a pointing axis. A pointing mechanism could be configured to adjust the pointing axis. The optical-communication component could be operable to communicate with a correspondent balloon via a free-space optical link. For example, the optical-communication component could include an optical receiver, transmitter, or transceiver. A controller could be configured to determine a predicted relative location of the correspondent balloon. The controller may control the pointing mechanism to adjust the pointing axis of the optical-communication component based on the predicted relative location so as to maintain the free-space optical link with the correspondent balloon. | 07-11-2013 |
20130179009 | Auto-Flight System Pilot Interface - An aircraft system comprising a display system, a graphical user interface, a first grouping of the controls in the graphical user interface, and a second grouping of the controls in the graphical user interface. The graphical user interface is configured to display controls on the display system. The controls are for commands sent to an auto-flight system in an aircraft that control flight of the aircraft. The first grouping of the controls is configured to control sending of the commands to the auto-flight system from a flight management system in the aircraft. The second grouping of the controls is configured to control sending of the commands to the auto-flight system from a user input to the graphical user interface. | 07-11-2013 |
20130184899 | METHOD FOR THE AUTOMATIC MONITORING OF AIR OPERATIONS NECESSITATING GUARANTEED NAVIGATION AND GUIDANCE PERFORMANCE - A method is disclosed for automatic monitoring of a flight management assembly of an aircraft implementing air operations necessitating guaranteed navigation and guidance performance, wherein flight path data generated by first and second flight management systems respectively, are compared in order to check their consistency; first and second flight management systems transmit their flight path data to a third flight management system; the third flight management system receives a current position of the aircraft, calculates deviations between this current position and a flight path depending on the flight path data received from the first and second flight management systems, which it utilizes only if they are identical, and calculates, according to these deviations, guidance commands for slaving onto this flight path. Monitoring can compare deviations and guidance commands received from the first second and third flight management systems in order to be able to detect an inconsistency between them. | 07-18-2013 |
20130184900 | VEHICLE ENERGY CONTROL SYSTEM WITH A SINGLE INTERFACE - A system for controlling energy of a vehicle, for example an aircraft, characterized in that it comprises:
| 07-18-2013 |
20130184901 | VEHICLE ENERGY AND POWER MANAGEMENT METHOD AND SYSTEM - A method of managing energy and/or power in a vehicle, including: one or more vehicle power systems adapted to control one or more power consuming components of the vehicle and one or more power producing components of the vehicle; and one or more propulsive power systems adapted to control a propulsive power unit of the vehicle. The method includes: proposing a vehicle route for a predetermined mission and/or destination; determining a time-based operational plan for each of the vehicle power consuming components; determining the power required by the vehicle power consuming components and the propulsive power required by the vehicle; determining the power required from the vehicle power producing components and the propulsive power required by the propulsive power unit as a function of time during the operational plan; and varying the proposed vehicle route and/or the operational plan to optimize a predetermined performance criterion for the vehicle. | 07-18-2013 |
20130190948 | AIRCRAFT RADIO SYSTEM - An aircraft radio system comprising a plurality of radios interconnected by a digital communications network, each radio having a transceiver and a dedicated processor platform, the aircraft radio system being configured to cause the dedicated processor platforms to constitute a virtual processing environment for the aircraft radio system. There is also an aircraft radio system comprising a plurality of discrete radios interconnected by a digital communications network, each radio having a transceiver, a dedicated processor platform and a server configured to support communications over the network using PPPoE, Point to Point Protocol over Ethernet, to provide a common digital interface between an aircraft domain and the radios for plural types of communication. | 07-25-2013 |
20130190949 | VEHICLE ENERGY CONTROL SYSTEM - A system for controlling energy of a vehicle, for example an aircraft, comprising a control interface able to be in at least one first and one second state, the first state being an instruction state in which the interface generates at least a first instruction for speed of variation of a current energy of the vehicle and the second state being a resting state in which it gives no instruction, the interface furthermore being configured to return into the second state after having been brought into the first state. | 07-25-2013 |
20130190950 | SYSTEM AND METHOD FOR PROVIDING AN AIRCRAFT NOISE ADVISORY DURING DEPARTURE AND ARRIVAL OF AN AIRCRAFT - A system and method for providing an aircraft noise advisory during departure and/or arrival of an aircraft are disclosed. In one embodiment, predefined allowable aircraft noise level information associated with a plurality of aircraft noise sensors located in the vicinity of airports are obtained. Further, predefined allowable aircraft noise level information associated with one or more of the plurality of aircraft noise sensors is presented on a display device in the aircraft, based on a current location of the aircraft, upon receiving noise data request from a pilot. Furthermore, current aircraft noise level information is obtained from one of the one or more aircraft noise sensors. In addition, the current aircraft noise level information is compared with predefined allowable aircraft noise level information associated with the one of the one or more aircraft noise sensors. Also, the aircraft noise advisory is displayed based on an outcome of the comparison. | 07-25-2013 |
20130197721 | METHOD FOR DETECTING PERFORMANCE OF AN AIRCRAFT BASED ON A CUSTOMIZED MESSAGE - The present invention relates to a method for detecting the performance of the aircraft comprising: collecting data reflecting operation status of the aircraft; generating the customized message based on the collected data, wherein, the customized message is configured to include one or more main parameters related to the operation status of the aircraft; storing or transmitting the customized message; and detecting the performance of the aircraft based on the customized message. | 08-01-2013 |
20130197722 | MULTI-AXIS SERIALLY REDUNDANT, SINGLE CHANNEL, MULTI-PATH FLY-BY-WIRE FLIGHT CONTROL SYSTEM - A multi-axis serially redundant, single channel, multi-path fly-by-wire control system comprising: serially redundant flight control computers in a single channel where only one “primary” flight control computer is active and controlling at any given time; a matrix of parallel flight control surface controllers including stabilizer motor control units (SMCU) and actuator electronics control modules (AECM) define multiple control paths within the single channel, each implemented with dissimilar hardware and which each control the movement of a distributed set of flight control surfaces on the aircraft in response to flight control surface commands of the primary flight control computer; and a set of (pilot and co-pilot) controls and aircraft surface/reference/navigation sensors and systems which provide input to a primary flight control computer and are used to generate the flight control surface commands to control the aircraft in flight in accordance with the control law algorithms implemented in the flight control computers. | 08-01-2013 |
20130197723 | INTEGRATED APPROACH NAVIGATION SYSTEM, METHOD, AND COMPUTER PROGRAM PRODUCT - Systems, computer program products, and methods for displaying navigation performance based flight path deviation information during the final approach segment to a runway and during landing of non-precision flight modes are provided. Improved graphical depictions of navigation performance based flight path deviation information provide pilots and flight crew members with clear, concise displays of the dynamic relationship between ANP and RNP, mode and aspect of flight and related procedures, intersecting flight paths, and current actual flight path deviation from a predefined flight path during the final approach segment to a runway and during landing. For example, an enhanced IAN display may include NPS-type deviation scales to show RNP/ANP relationships and predetermined RNP markers to alert the pilots and flight crew members that the FMC has transitioned from an NPS display for RNAV (LNAV/VNAV) flight procedures to an enhanced IAN display for a non-precision (non-xLS) approach and/or landing. | 08-01-2013 |
20130204467 | Wind Calculation System Using a Constant Bank Angle Turn - A method and apparatus for operating an aircraft. The aircraft is flown at a constant bank angle in which the aircraft crosses an intended ground track for the aircraft. Information is identified about a wind using positions of the aircraft flying at the constant bank angle. | 08-08-2013 |
20130204468 | METHOD AND A DEVICE FOR PERFORMING A HEALTH CHECK OF A TURBINE ENGINE OF AN AIRCRAFT HAVING AT LEAST ONE SUCH ENGINE - A method of performing a health check of at least one turbine engine ( | 08-08-2013 |
20130204469 | SYSTEM AND METHOD FOR REAL-TIME AIRCRAFT PERFORMANCE MONITORING - A computer apparatus and method to determine aircraft fuel mileage performance. The computer apparatus including a memory and a processor disposed in communication with the memory and configured to issue a plurality of instructions stored in the memory. The instructions issue signals to receive real-time aircraft data during aircraft flight and process the real-time data to determine real-time aircraft mass data. A calculation is performed to determine the real-time fuel mileage performance for the aircraft based upon determined real-time aircraft mass data. | 08-08-2013 |
20130211629 | DISPLAY SYSTEM - A display system for displaying a layout of controls in a simulator including at least one of an information display, a switch such as a toggle or push-button switch, and a monitoring device such as an indicator, or a gauge, for a vehicle, the display system including a touch sensitive screen which is generally transparent over a significant portion of its area, and a plurality of projectors which project onto a back of the screen, images of the vehicle controls, the projectors each being operatively connected to a computer controller which responds to the front of the screen being touched where a depicted control is displayed, to change the display in a manner to mimic the result of a corresponding actual vehicle control being operated. | 08-15-2013 |
20130211630 | FORCE GENERATOR FOR MOUNTING ON A STRUCTURE - The invention relates to a force generator ( | 08-15-2013 |
20130211631 | Integrated Aircraft Flight Control Units - According to one embodiment, an integrated aircraft trim assembly features a shaft, a mechanical stop, a trim motor, a clutch, and a measurement device. The mechanical stop device is operable to at least partially prevent rotation of the shaft outside of an allowable range of motion. The trim motor has an output component in mechanical communication with the shaft. The clutch separates the trim motor from the shaft. The measurement device is proximate to the shaft and operable to measure a position of the shaft and communicate the measured position to a flight control computer operable to change a position of a flight control device. | 08-15-2013 |
20130211632 | Detection of aircraft descent anomaly - An aircraft ground or sea approach anomaly detection method. The method includes the steps of characterizing a flight phase of the aircraft, determining a prohibited flight envelope, defining a set of prohibited vertical speeds of the aircraft for given altitudes in relation to the ground or the sea, as a function of the flight phase of the aircraft characterized, and detecting a ground approach anomaly of the aircraft as a function of a current vertical speed and altitude in relation to the ground or the sea of the aircraft, in relation to the prohibited flight envelope determined. | 08-15-2013 |
20130211633 | SENSOR FOR DETECTING HYDRAULIC LIQUIDS IN AIRCRAFT - The present invention relates generally to a system that monitors the condition of hydraulic systems for an aircraft or for other applications and, more particularly, to a system and method for detecting leakage within the hydraulic system aboard an aircraft. Such system is detecting hydraulic liquids by extended sensors based on the collapse of percolation conductivity (COPC) which sensors are covering an area in the aircraft. | 08-15-2013 |
20130218372 | Weapons Stores Processor Panel For Aircraft - An aircraft weapons control system including a weapons stores processor panel for receiving input signals from a weapons input; a weapons interface for receiving fire signals from the weapons stores processor panel to control firing of aircraft weapons; and a flight management system in communication with the weapons stores processor panel and the weapons interface, the flight management system providing control signals to the weapons interface; wherein the weapons stores processor panel implements safety interlocks to prevent or enable firing of the aircraft weapons | 08-22-2013 |
20130226373 | METHODS FOR IN-FLIGHT ADJUSTING OF A FLIGHT PLAN - A method of in-flight adjusting a flight plan of an aircraft to provide a low cost flight based on predicting a trajectory for completion of the flight based on at least the current state data of the aircraft along the flight plan, performance data for the aircraft, and the flight plan data, and computing the cost of completing the flight plan. | 08-29-2013 |
20130226374 | Yaw Damping System And Method For Aircraft - An alternative system for damping the dutch roll mode in an aircraft is provided using roll control surfaces. Classical yaw dampers for the dutch roll mode utilize the yaw control surfaces such as a rudder to dampen the dutch roll mode oscillations. An alternative damper is described that utilizes roll control surfaces such as spoilers or ailerons to dampen the dutch roll mode. | 08-29-2013 |
20130231803 | Four-Dimensional Flyable Area Display System for Aircraft - A method and apparatus for displaying information for an aircraft. Information is identified for the aircraft. An aeronautical chart is displayed on a display system. An envelope is displayed in the aeronautical chart based on the information. The envelope defines a space flyable by the aircraft that meets a number of objectives. | 09-05-2013 |
20130238170 | AUTONOMOUS VEHICLE AND METHOD FOR COORDINATING THE PATHS OF MULTIPLE AUTONOMOUS VEHICLES - A method for coordinating the paths of multiple autonomous vehicles and a vehicle configured to coordinate its path with the path(s) of other vehicles so as to enhance cooperation between the vehicles. The method also enables the vehicles to perform their respective missions more efficiently. The method is applicable to any system in which multiple autonomous vehicles may need to coordinate their paths with each other. | 09-12-2013 |
20130238171 | METHOD AND DEVICE FOR DISPLAYING SPEED INFORMATION ON AN AIRCRAFT - The display device ( | 09-12-2013 |
20130245859 | METHOD AND APPARATUS FOR CONVERSION OF GPS HEADING DATA FOR USE BY ELECTRONIC FLIGHT DIRECTOR - An improved Horizontal Situation Indicator (HSI) module for use with an aircraft, wherein the HSI module is adapted for accepting Bank Angle Commands or waypoint data from the GPS flight module and for using the same to determine a heading error. The HSI module is further adapted for outputting the heading error to the Flight Director module where it can be used to create a Roll Command for output to the Auto-Pilot, whereby the Auto-Pilot can be commanded to follow a turn using the HSI and the Flight Director without requiring an additional module be added to the aircraft to create the heading error for use by the Flight Director. The waypoint data can be of the “flyover” type or the “flyby” type. | 09-19-2013 |
20130253734 | SPEED CONTROL FOR A FIXED PTICH RAM AIR TURBINE - A system of speed control for a ram air turbine of an aircraft includes a power electronics controller, at least one routing device in communication with the power electronics controller, at least one secondary load in serial communication with the at least one routing device and the power electronics controller, and a ram air turbine (RAT) in communication with the power electronics controller, wherein the power electronics controller is configured to apply the secondary load to the RAT through the at least one routing device in response to a transient speed increase of the RAT. | 09-26-2013 |
20130253735 | DISTRIBUTED ELECTRONIC ENGINE CONTROL ARCHITECTURE - A distributed electronic control system for an aircraft includes an engine data controller arranged on an airframe of the aircraft and a plurality of engine data concentrators arranged proximate an engine of the aircraft in signal communication with the engine data controller. The engine data controller is configured to process information related to the engine of the aircraft, the plurality of engine data concentrators are configured to receive engine sensor information from a plurality of engine sensors, and the plurality of engine data concentrators are further configured to transmit the engine sensor information to the engine data controller. | 09-26-2013 |
20130253736 | ELECTROMECHANICAL BRAKING SYSTEM FOR AN AIRCRAFT - The invention relates to an aircraft braking system having brakes with electromechanical braking actuators (103) adapted to press selectively against associated stacks of disks in order to generate a braking torque on associated wheels of the aircraft; at least one control module (130) receiving braking setpoints and responding by generating a braking command (121); and at least one power module (120) responding to the braking command by delivering AC power to the motors of actuators connected to the power module so that the motors develop a braking force corresponding to the braking setpoints. According to the invention, the control module includes a digital processor stage (131) and an analog processor unit (135). | 09-26-2013 |
20130253737 | MULTI CORE VEHICLE MANAGEMENT UNIFIED USER INTERFACE SYSTEM AND METHOD - A computerized method for providing a unified user interface to a plurality of flight management components encapsulated within a flight management system. The method can include receiving a flight management system input dataset from a first flight management system user interface device. The method can also include creating, with a processor programmed to provide a unified user interface, a plurality of flight management system input data portions to be transmitted to a plurality of destination flight management system components. The plurality of flight management system input data portions can be based on the flight management system input dataset and each flight management system input data portion can correspond to one of said plurality of destination flight management system components. Each of said plurality of flight management system input data portions can be transmitted from the processor to said corresponding destination flight management system component. | 09-26-2013 |
20130261847 | Information Handling for Aircraft Flight Decks - A system and method for handling information for use on a flight deck network on an aircraft. Information is received from a number of information sources. The number of information sources is not part of the flight deck network. The flight deck network is a certified network. It is determined whether the information is approved to be used on the flight deck network. A manner in which the information is allowed to be used on the flight deck network is also determined. Responsive to a determination that the information is approved to be used on the flight deck network, the information is sent to the flight deck network during operation of the aircraft. | 10-03-2013 |
20130261848 | SYSTEMS AND METHODS FOR PROVIDING NONPROTECTED-AREA AWARENESS AND ALERTING - Systems and methods for providing nonprotected-area awareness and alerting to a crew of a vehicle. An exemplary system determines a safe region based on the received previously defined route based on controlling authority requirements associated with the route, identifies at least one non-safe region based on the determined safe region and then uniquely presents the identified at least one non-safe region on a display such as a moving map display (2D or 3D). | 10-03-2013 |
20130261849 | SEARCHLIGHT LOCATION SYSTEM - Systems and methods for identifying a location illuminated by an onboard searchlight on a vehicle are presented. A location of interest is illuminated at an illuminated location illuminated by the onboard searchlight, and a vehicle position of the vehicle and the onboard searchlight is determined. A vehicle orientation of the vehicle is determined based on a pitch, roll, and yaw of the vehicle, and an azimuth and an elevation of the onboard searchlight light is recorded to provide a recorded azimuth and elevation data. A pointing coordinate for the onboard searchlight illuminating the illuminated location is computed based on the vehicle orientation, the vehicle position, and the recorded azimuth and the elevation data, and the illuminated location is calculated based on the pointing coordinate. | 10-03-2013 |
20130261850 | Instruction Visualization System - A method and apparatus comprising an instruction analyzer. The instruction analyzer is configured to receive a movement instruction for an aircraft during movement of the aircraft. The instruction analyzer is further configured to generate a number of volumes of airspace defining a desired movement of the aircraft using the movement instruction during the movement of the aircraft. | 10-03-2013 |
20130261851 | AVIONICS CONTROL AND DISPLAY UNIT HAVING CURSOR CONTROL MODE OF OPERATION - An avionics control and display unit (CDU) in an integrated avionics system includes a display unit having a touch screen configured to detect touch input. The CDU is configured to have a first mode of operation or a second mode of operation. When the first mode of operation is selected, the display unit is configured to display control indicia to facilitate the control of one or more functions associated with the avionics system. When the second mode of operation is selected, the display unit is configured to enable a cursor control area to facilitate manipulation of indicia displayed by a display device such as a primary flight display (PFD) or a multifunction display (MFD), and so forth, via touch input to the touch screen over the cursor control area. | 10-03-2013 |
20130261852 | MONITORING DEVICE FOR AN ACTUATION SYSTEM OF AN AIRCRAFT, ACTUATION SYSTEM AND METHOD FOR RECONFIGURING THE ACTUATION SYSTEM - A monitoring device is disclosed for an actuation system of an aircraft for monitoring a guiding device of a regulating flap with a load sensor. An actuation system with the monitoring device and a method for reconfiguring such an actuation system are disclosed. The monitoring device includes an interface to the load sensor and an interface to a driving device for adjusting the regulating flap. The monitoring device can determine or receive in-flight information actively signaling a predefined flight attitude and/or a predefined operational state of the aircraft. The monitoring device can compare a load value corresponding to a sensor value acquired by the load sensor and a limiting value corresponding to a minimum operational load for the predefined flight attitude and/or the predefined operational state of the aircraft and a monitoring function. The monitoring function can assign a fault mode to the regulating flap. | 10-03-2013 |
20130261853 | VEHICLE MANAGEMENT SYSTEM USING FINITE STATE MACHINES - A system includes a plurality of actuators and a management system operably associated with the plurality electronic and mechanical devices. The management architecture includes interfaces configured to the entire electronics and mechanics to provide a parameter to a computer. The computer includes a control and management architecture using modular finite state flow designs configured to analyze the parameter. The computer with a plurality of finite state machines can conduct a plurality of control laws operably associated with one or more actuators for finite functions of mobility. The method includes matching the parameter with the finite state machine and controlling the actuator via control law operably associated with finite state machine. The method can therefore be achieved either manually, semi-autonomously and autonomously with seamless and switchless control using a central control computer with integration of electronic and mechanic sensors and devices. | 10-03-2013 |
20130268146 | METHOD AND A DEVICE FOR ADAPTING THE MAN-MACHINE INTERFACE OF AN AIRCRAFT DEPENDING ON THE LEVEL OF THE PILOT'S FUNCTIONAL STATE - A method of adapting a man-machine interface ( | 10-10-2013 |
20130274961 | Self Tuning Vibration Isolation System - A system and method to isolate vibrations from a vibrating structure. The system includes an adjustable vibration isolator that creates a reacting force matching the vibratory force of the vibrating structure. The method includes continuously monitoring the reacting force and vibratory force with a sensor system operably associated with a control unit having an algorithm to determine if adjustment of the vibration isolator is required. If required, the control unit commands a driver to selectively adjust the vibration isolator. | 10-17-2013 |
20130274962 | Standby Aircraft Management System - A method and apparatus for operating an aircraft. An aircraft system comprises a housing, a standby aircraft management system, and a backup power system. The standby aircraft management system is associated with the housing and is configured to provide communications, navigation, and control of a number of aircraft systems needed for safe flight and landing of an aircraft in which the standby aircraft management system is located. The backup power system is configured to supply power to the standby aircraft management system when the power is unavailable from the aircraft. | 10-17-2013 |
20130274963 | EXTENSION OF THREE LOOP CONTROL LAWS FOR SYSTEM UNCERTAINTIES, CALCULATION TIME DELAY AND COMMAND QUICKNESS - A system includes a plurality of actuators and a control system operably associated with the plurality of actuators. The control system having a control logic architecture having a dynamic command input shaping model associated with an input command, a robust inner loop associated with the dynamic command input shaping model, and a time delay cancellation model. The method includes selecting a control law based upon a flight performance of an aircraft, decoupling the control law into a first individual component and a second individual component of the aircraft flight motion, analyzing each individual component separately, regrouping the component of flight motion, analyzing the control law with a time delay cancellation model and providing the necessary dynamic flight quickness with a different command input condition. | 10-17-2013 |
20130282204 | Self Tuning Vibration Absorber - A system and method to adjustably create a reacting force in response to a vibrating force of a vibrating structure. The system includes an adjustable vibration absorber that creates a range of reacting forces. The method includes continuously monitoring the reacting force and the vibrating force with a sensor system operably associated with a control unit having an algorithm to determine if adjustment of the vibration absorber is required. If required, the control unit commands a driver to selectively adjust the vibration absorber such that the reacting force equals the vibrating force. | 10-24-2013 |
20130282205 | STANDBY INSTRUMENT FOR AN AIRCRAFT, THE INSTRUMENT PROVIDING FLIGHT INFORMATION, POWER MARGIN INFORMATION, AND ASSISTANCE IN PILOTING - A standby instrument ( | 10-24-2013 |
20130282206 | METHOD AND DEVICE FOR CONFIGURING AN ALERTS MANAGEMENT SYSTEM FOR AN AIRCRAFT - A method and a device for configuring an alerts management system for an aircraft comprises: generating a list of a plurality of alerts and of resolution procedures for an aircraft; for each alert, defining: distinctive characteristics of the alert; logic for detecting the alert; at least one procedure for resolving the alert; and, for each alert, defining recording in a dedicated alerts file the set of information defined for said alert, the alerts file having a structure and a format of data that are predefined for the alerts and the procedures; determining existing links between the dedicated alerts files; and in response to the determining step, updating the content of the dedicated alerts files according to the links identified. | 10-24-2013 |
20130289802 | SYSTEM AND METHOD FOR CONFIGURING A DIRECT LIFT CONTROL SYSTEM OF A VEHICLE - A system and methods for configuring a direct lift control system of a vehicle are presented. A plurality of fly-by-wire control surfaces is provided, and fly-by-wire control surface deflection commands of the fly-by-wire control surfaces are scheduled. The fly-by-wire control surfaces are symmetrically actuated based on the fly-by-wire control surface deflection commands such that a fluid dynamic lift of the vehicle is modulated without using a short-period pitch control. | 10-31-2013 |
20130289803 | METHOD FOR EVALUATING THE STRUCTURAL COMPATIBILITY OF AN AIRCRAFT FOR USE ON ROUGH RUNWAYS - A method for evaluating the structural compatibility of an aircraft for use on a runway having a profile with one or more roughnesses in the form of bumps and/or dips, comprising the steps of: generating a first bump height curve representing elevations or depressions on the runway; comparing the bump height curve with a second bump height curve which is a first reference curve; generating a first power spectral density curve of the profile of the runway; comparing the first power spectral density curve with a second power spectral density curve which is a second reference curve; authorizing or denying the aircraft the use of the runway on the basis of results of the comparison between the bump height curve and the first reference curve, and between the power spectral density curve and the second reference curve. | 10-31-2013 |
20130297101 | AIRCRAFT ELECTRIC BRAKE ACTUATION SYSTEM AND METHOD - A system and method of controlling aircraft brakes in an aircraft that includes a brake pedal and an electric brake actuator. An aircraft operational state is determined and an application force that is supplied to the brake pedal is determined When the determined aircraft operational state is a ground-idle state and the determined application force is greater than a set force magnitude, an actuator brake is moved to engage the electric brake actuator and the electric brake actuator is de-energized. | 11-07-2013 |
20130297102 | ELECTRIC TAXI AUTO-GUIDANCE AND CONTROL SYSTEM - An auto-guidance and control method and system is provided for use in conjunction with an aircraft electric taxi system. Aircraft status data is obtained, and airport feature data accessed. A processor generates taxi path guidance and control information including at least taxi speed guidance information, and sends commands derived from the taxi speed guidance information by the processor directly to an electric taxi controller to regulate the taxi speed of the aircraft. | 11-07-2013 |
20130304282 | APPARATUS FOR UNMANNED VEHICLE - An apparatus and a method are disclosed, such as an apparatus wholly or partially mounted on an unmanned vehicle and arranged to act upon a payload, the payload being mounted on the unmanned vehicle and, under an action of the apparatus, being changeable from being in a first state to being in a second state. The method can include: receiving an instruction that the unmanned vehicle, with the payload mounted thereon, is to travel to a location; determining that the payload is in the first state; and responsive to determining that the payload is in the first state: opposing the payload being changed to being in the second state; and providing, for an entity remote from the unmanned vehicle, an indication that the payload is in the first state. | 11-14-2013 |
20130311005 | SYSTEMS AND METHODS FOR REFLECTED INERTIA PARKING BRAKE - Systems and methods are disclosed for parking brake systems for use in, for example, an aircraft. In this regard, a system is provided comprising a parking brake system for an aircraft comprising an electric motor coupled to a high gear ratio transmission, a first clutch for engaging the electric motor to a propulsion transmission, and a second clutch for engaging propulsion transmission to an aircraft wheel. The high gear ratio transmission has a gear ratio sufficient to maintain the aircraft wheel in a stationary position. | 11-21-2013 |
20130311006 | TRIPLEX COCKPIT CONTROL DATA ACQUISITION ELECTRONICS - A system and method are provided for controlling aircraft flight control surfaces. The system may include at least three pilot sensor channels, each pilot sensor channel including a set of pilot sensor data. The system may also include at least three aircraft sensor channels, each aircraft sensor channel including a set of aircraft sensor data. The system may further include an actuator control component configured to synchronously receive and vote on the pilot sensor data and the aircraft sensor data, such that a voted output of the at least three pilot sensor channels is transmitted to a flight control computer and augmented before being transmitted to remote electronics units. The voted output of the at least three pilot sensor channels providing for the control of the aircraft surfaces coupled to the remote electronics units. | 11-21-2013 |
20130311007 | Aircraft Information Management System - A method and apparatus comprising an existing aircraft node and an information agent located in the existing aircraft node. The existing aircraft node is connected to a number of aircraft systems and a network in an aircraft network data processing system. The information agent is configured to provide access to information received by the existing aircraft node to other aircraft nodes in the aircraft network data processing system. | 11-21-2013 |
20130311008 | Personal Aircraft - A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight. | 11-21-2013 |
20130311009 | FLIGHT TECHNICAL CONTROL MANAGEMENT FOR AN UNMANNED AERIAL VEHICLE - Two architectures for unmanned aerial vehicles (UAVs) and a method for executing a mission plan are provided. One architecture for a UAV includes a flight command and mission execution (FCME) component making strategic decisions, a flight technical control manager (FTCM) making tactical decisions and a vehicle management system (VMS) providing navigational support. The FCME and FTCM execute on one processor and the VMS executes on a separate processor. The second architecture includes redundant processors for executing the FCME and FTCM as well as redundant processors for executing the VMS. The UAV executes a mission plan, which may include flight plan(s), communication plan(s), weapons plan(s), sensor plan(s), and/or contingent flight plan(s). The UAV may control various optical sensors, training sensors, and lights as well. | 11-21-2013 |
20130311010 | METHOD AND SYSTEM FOR PILOTING A FLYING CRAFT WITH REAR PROPULSION UNIT - According to the invention, in accordance with a servo loop, the attitude (θ | 11-21-2013 |
20130311011 | DYNAMIC LIMITATION OF MONOBLOCK FLIGHT CONTROL SURFACES INCLINATIONS DURING STALL SUSCEPTIBILITY CONDITIONS - Method for dynamically limiting the inclinations of monoblock flight control surfaces (FCS) in an aircraft. Dynamic limitation of the FCS is activated if a stall susceptibility condition is detected in the current aircraft environment. The real-time calibrated airspeed of the aircraft, real-time angle of attack (AOA) of the aircraft, and real-time sideslip angle (AOS) of the aircraft are obtained. The aircraft parameters may be obtained via estimation if the measured values are deemed unsuitable. The real-time local AOA and AOS of the FCS are calculated based on the obtained aircraft parameters. The inclination of each of the FCS relative to the critical values is dynamically limited according to the calculated real-time local AOA and AOS of the FCS. The aircraft may be an unmanned aerial vehicle (UAV) and/or a V-tail aircraft. The stall susceptibility condition may include icy conditions. | 11-21-2013 |
20130311012 | ROTARY WING AIRCRAFT VIBRATION CONTROL SYSTEM WITH RESONANT INERTIAL ACTUATORS - A control system for resonant inertial actuators estimates operating parameters of the resonant inertial actuators based on voltage and current feedback and dynamically limits selected parameters to maintain the safe, efficient, and cost effective operation of the resonant inertial actuators. Resistance within the electrical drives for the resonant inertial actuators is estimated from the voltage and current feedback and in conjunction with the modeling of the resonant inertial actuators other operating parameters are calculated or otherwise estimated. Having regard for the responsiveness of the resonant inertial actuators to changes in command signals, the command signals are adjusted to dynamically limit the estimated parameters. | 11-21-2013 |
20130317669 | Acoustic Ranging System Using Atmospheric Dispersion - A method and apparatus for processing sound from a sound source. The sound from the sound source is detected. Harmonics in the sound from the sound source are identified. A distance to the sound source is identified using the harmonics and a number of atmospheric conditions. | 11-28-2013 |
20130317670 | PROVIDING A DESCRIPTION OF AIRCRAFT INTENT - The present disclosure provides a computer-implemented method of generating a description of aircraft intent expressed in a formal language that provides an unambiguous description of an aircraft's intended motion and configuration during a period of flight. A flight intent description is parsed to provide instances of flight intent that span a flight segment, the flight segments together spanning the period of flight. The parsed flight intent is converted into parametric aircraft intent by generating an associated flight segment description for each flight segment that comprises instances of flight intent to close all associated degrees of freedom of motion and of configuration of the aircraft. At least some flight segment descriptions contain a parameter range, and the method further comprises optimising the parametric aircraft intent by determining an optimal value for the parameter of each parameter range. | 11-28-2013 |
20130317671 | PROVIDING A DESCRIPTION OF AIRCRAFT INTENT - The present disclosure provides a computer-implemented method of generating a description of aircraft intent expressed in a formal language that provides an unambiguous description of an aircraft's intended motion and configuration during a period of flight. A description of flight intent is parsed to provide instances of flight intent, each instance of flight intent spanning a flight segment. For each flight segment, an associated flight segment description is generated that comprises one or more instances of flight intent that describe the aircraft's motion in at least one degree of freedom of motion. Flight segment descriptions are compared with constraints and/or objectives and the associated flight segment descriptions are enriched with information describing relevant constraints and/or objectives. The enriched flight intent is converted into aircraft intent by ensuring that the flight segment descriptions close all degrees of freedom of the aircraft during the period of flight. | 11-28-2013 |
20130317672 | PROVIDING A DESCRIPTION OF AIRCRAFT INTENT - The present disclosure provides a computer-implemented method of generating a description of aircraft intent expressed in a formal language that provides an unambiguous description of an aircraft's intended motion and configuration during a period of flight. A description of flight intent is parsed to provide instances of flight intent, each instance of flight intent spanning a flight segment. For each flight segment, an associated flight segment description is generated that comprises one or more instances of flight intent that describe the aircraft's motion in at least one degree of freedom of motion. One or more instances of flight intent are added to flight segments to close all degrees of freedom of motion. The flight segment descriptions are collated thereby providing a description of aircraft intent for the period of flight expressed in a formal language. | 11-28-2013 |
20130325212 | AERIAL VEHICLE WITH MISSION DURATION CAPABILITY DETERMINATION - An aerial vehicle can include oil sensors connected to a lubrication system and a computer connected to the oil sensors. The computer can be programmed to determine mission duration for the unmanned aerial vehicle, determine a maximum oil system duration for the unmanned aerial vehicle based upon data from the oil sensors, perform a comparison of the mission duration to the maximum oil system duration, and output a signal based upon the comparison. | 12-05-2013 |
20130325213 | LDV for Airdrops - A method of using a light detection system for increasing the accuracy of a precision airdrop is described. Radiation is transmitted to target areas between an airborne vehicle and a dropzone target. Scattered radiation is received from the target areas. Respective wind characteristics are determined from the scattered radiation and a wind velocity map is generated, based on the respective wind characteristics, between the airborne vehicle, and at least the dropzone target. An aerial release point for the precision airdrop is computed based on the generated wind velocity map and a location of the dropzone target. | 12-05-2013 |
20130325214 | SYSTEM AND METHOD FOR CONTROLLING POWER IN A HYBRID VEHICLE USING COST ANALYSIS - A system for controlling power of a hybrid vehicle may include a controller configured to receive a signal indicative of a commanded acceleration for the hybrid vehicle and determine a potential for each of a power source, a generator, and an energy storage device to supply energy to achieve the commanded acceleration. The controller may be further configured to determine a cost associated with using each of the power source, the generator, and the energy storage device to achieve the commanded acceleration, and determine a combination of the power source, the generator, and the energy storage device that achieves the commanded acceleration at a lowest total cost. The controller may also be configured to provide a signal to at least one of the power source, the generator, and the energy storage device to achieve the commanded acceleration based on the determined combination. | 12-05-2013 |
20130325215 | SYSTEM AND METHOD FOR DEVELOPING DYNAMIC POSITIONAL DATABASE FOR AIR VEHICLES AND TERRAIN FEATURES - A system for creating a digital representation of a status of one or more air vehicles and of sensed external objects includes one or more air vehicles, one or more sensors coupled to each of the one or more air vehicles, and a processor. The processor is configured to determine navigation information associated with travel of each of the one or more air vehicles, and capture data associated with the sensed external objects sensed by the one or more sensors. The processor is further configured to identify and track the sensed external objects in the captured data, geo-locate the identified sensed external objects via dynamic landmarking, and dynamically update a landmark database. The processor is further configured to utilize the landmark database to control at least one or more functions in a respective air vehicle of the one or more air vehicles. | 12-05-2013 |
20130325216 | SYSTEM AND METHOD FOR AUTHORIZING STOPPAGE OF PILOTING TASKS - A system and method for authorizing stoppage of piloting tasks performed by at least one pilot of an aircraft equipped with automatic piloting means is disclosed. A duration for which the stoppage is authorized is determined, the duration being determined based on the calculation of an instant of commencement of a next action, and the next action being an action not yet carried out that must be carried out first by the pilot. The duration is then displayed. | 12-05-2013 |
20130332010 | WIRELESS ENGINE MONITORING SYSTEM WITH MULTIPLE HOP AIRCRAFT COMMUNICATIONS CAPABILITY AND ON-BOARD PROCESSING OF ENGINE DATA - An engine monitoring module includes a housing configured to be mounted at the aircraft engine and a first wireless transmitter carried by the housing. A memory is carried by the housing and a processor is carried by the housing and coupled to the memory and the first wireless transmitter and configured to collect and store in the memory engine data relating to at least one engine parameter sensed during operation of the aircraft engine by a plurality of engine sensors that transmit the engine data via the first wireless transmitter. A wireless receiver is located within the aircraft and configured to receive the engine data transmitted from the first wireless transmitter. A second wireless transmitter is located within the aircraft and operatively connected to the wireless receiver and configured to receive and transmit the engine data. | 12-12-2013 |
20130332011 | WIRELESS ENGINE MONITORING SYSTEM AND ASSOCIATED ENGINE WIRELESS SENSOR NETWORK - A plurality of wireless engine sensors each includes a sensing circuit that senses an engine parameter as engine data. A radio transceiver receives and transmits the engine data regarding the sensed engine parameters. An engine monitoring module includes a housing configured to be mounted at the aircraft engine. A sensor receiver is mounted within the housing and receives the engine data from the wireless engine sensors. A first wireless transmitter is carried by the housing. A memory is carried by the housing and a processor is carried by the housing and coupled to the memory and the first wireless transmitter and configured to collect and store in the memory engine data related to engine parameters sensed during operation of the aircraft engine by the plurality of wireless engine sensors and transmit the engine data via the first wireless transmitter. | 12-12-2013 |
20130338857 | Aircraft Passenger Health Management - A method and apparatus for managing health of a passenger on an aircraft. A physiological condition of the passenger seated in a seat in a cabin in the aircraft is monitored using a passenger condition sensor to provide passenger condition information. An environmental condition in the cabin is monitored using a cabin condition sensor to provide cabin condition information. The passenger condition information and the cabin condition information are processed to provide passenger health information. The passenger health information is displayed to the passenger. | 12-19-2013 |
20130338858 | METHOD FOR THREE DIMENSIONAL PERCEPTION PROCESSING AND CLASSIFICATION - An apparatus is described comprising at least one processor; and memory storing instructions that, when executed by the at least one processor, cause the apparatus to: organize items of raw data received from at least one sensor of a vehicle as a first data structure, organize classified data objects as a second data structure, and link at least one item of the first data structure to at least one object of the second data structure. | 12-19-2013 |
20130338859 | AIRCRAFT CONTROL SYSTEM, AIRCRAFT, AIRCRAFT CONTROL PROGRAM, AND METHOD FOR CONTROLLING AIRCRAFT - A control system of an aircraft includes a computer that controls flight based on either a flight control law that controls flight by controlling the deflection angles of control surfaces or a control surface/thrust integrated flight control law that controls flight by controlling the deflection angles of the control surfaces and engine thrust, and a control surface failure/damage detection device. If malfunctioning of the control surface(s) is detected, the deflection angles and the rates of change of the deflection angles of the control surfaces are calculated based on the detection result, and the necessity of switching from the flight control law to the control surface/thrust integrated flight control law is judged by judging whether or not the calculated deflection angles or rates of change of the deflection angles exceed an acceptable range of change. | 12-19-2013 |
20130345904 | METHODS AND SYSTEMS FOR IMPLEMENTING SOFTWARE-SELECTABLE MULTIPURPOSE AIRCRAFT PINS - An avionics system configurable through software to support more than one pin-out design. An exemplary system includes configuration pins that receive one or more signals from an external source, one or more subcircuits, one or more multipurpose input/output pins, a controller that determines a configuration mode based on one or more received signals, and a selection circuit that connects one of the subcircuits with one or more of the multipurpose input/output pins, based on the determined configuration mode. | 12-26-2013 |
20130345905 | AVIONICS DISPLAY SYSTEM PROVIDING ENHANCED FLIGHT-PLAN MANAGEMENT - A method of executing a task associated with a flight plan displayed on a navigation display in the form of a graphical image comprises selecting the task, generating symbology on the display graphically representative of the task to be executed and characterized by at least one parameter, and adjusting at least a portion of the symbology by dragging on the display to achieve a desired value of the at least one parameter. | 12-26-2013 |
20130345906 | METHODS AND SYSTEMS FOR TAXIWAY TRAFFIC ALERTING - Systems and methods for providing the crew of a vehicle with a potential collision alert. The alert is based on presumed flight-crew action and reaction times, ownship speed, and required distance to safely stop the ownship before intersection with traffic. An exemplary system located aboard an ownship includes a communication device that receives information from a ground traffic; a memory device that stores ownship information and predefined constants; and a processing device that determines a distance to the traffic when the traffic passes the ownship after the ownship stops at a estimated full-stop location, based on the received ownship information and the predefined constants, determines distance to the ground traffic vehicle, based on the determined point in time, and generates a potential collision alert if the determined distance is less than a predefined safe distance value. An exterior lighting device outputs a visual illumination after the potential collision alert is generated. | 12-26-2013 |
20130345907 | METHOD FOR AUTOMATIC YAW AXIS CONTROL FOR AIRCRAFT WITH MECHANICAL FLIGHT CONTROLS - A method for automatic yaw axis control in aircraft with mechanical controls, said aircraft including a yaw actuator to control orientation of a yaw control surface and deliver a measured value of the torque on the control surface, a yaw trim actuator driving movement of a yaw trim control surface limiting the force applied by the yaw actuator to orient the yaw control surface, and sensors supplying an estimate of a lateral yaw force, includes calculating a setpoint value for the position of the yaw control surface determined by the estimated lateral force, an estimated torque of the yaw actuator determined by the measured value of the torque of the yaw actuator and a measured position of the yaw control surface, the estimated torque calculated having a lower oscillation dynamic range than the measured torque, and a trim command for activating/deactivating the yaw trim actuator determined by the estimated torque. | 12-26-2013 |
20140005861 | METHOD AND DEVICE FOR ASSISTING THE MISSION TRACKING OF AN AIRCRAFT | 01-02-2014 |
20140005862 | Method and Apparatus for Aircraft Sensor and Actuator Failure Protection Using Reconfigurable Flight Control Laws | 01-02-2014 |
20140012436 | METHOD FOR AIDING NAVIGATION MAKING IT POSSIBLE TO MANAGE A VERTICAL CONSTRAINT IN AN ANTICIPATED MANNER - A method for aiding navigation is provided, implemented in a flight management system, for the construction of a vertical trajectory of an aircraft following a predetermined lateral trajectory between a departure point and an arrival point; the departure point and arrival point furthermore being characterized by predefined altitudes, respectively H | 01-09-2014 |
20140018978 | SYSTEMS AND METHODS FOR DRAGGING BRAKE DETECTION - Systems and methods are disclosed for detection of dragging brakes for use in, for example, an aircraft. A method is provided comprising calculating, by a brake controller, a slip ratio based upon an aircraft speed and a speed of an aircraft wheel, determining, by the brake controller, that the slip ratio is above a threshold value, and sending, by the brake controller and in response to the slip ratio being above the threshold value, a dragging brake signal to an aircraft component. | 01-16-2014 |
20140018979 | AUTONOMOUS AIRSPACE FLIGHT PLANNING AND VIRTUAL AIRSPACE CONTAINMENT SYSTEM - Devices, systems, and techniques for generating a graphical user interface including a three-dimensional virtual containment space for flight of an unmanned aerial vehicle (UAV) are described. In some examples, the graphical user interface may be generated based on user input defining a virtual boundary for the flight of the UAV. | 01-16-2014 |
20140025233 | UNMANNED DEVICE UTILIZATION METHODS AND SYSTEMS - Structures and protocols are presented for configuring an unmanned aerial device to perform a task, alone or in combination with other entities, or for using data resulting from such a configuration or performance. | 01-23-2014 |
20140025234 | UNMANNED DEVICE UTILIZATION METHODS AND SYSTEMS - Structures and protocols are presented for configuring an unmanned aerial device to perform a task, alone or in combination with other entities, or for using data resulting from such a configuration or performance. | 01-23-2014 |
20140025235 | UNMANNED DEVICE UTILIZATION METHODS AND SYSTEMS - Structures and protocols are presented for configuring an unmanned aerial device to perform a task, alone or in combination with other entities, or for using data resulting from such a configuration or performance. | 01-23-2014 |
20140025236 | UNMANNED DEVICE UTILIZATION METHODS AND SYSTEMS - Structures and protocols are presented for configuring an unmanned aerial device to perform a task, alone or in combination with other entities, or for using data resulting from such a configuration or performance. | 01-23-2014 |
20140025237 | FLIGHT CONTROL LAWS FOR CONSTANT VECTOR FLAT TURNS - An aircraft and method to control flat yawing turns of the aircraft while maintaining a constant vector heading across a ground surface. The aircraft includes a control system in data communication with a model, a lateral control architecture, a longitudinal control architecture, and an initialization command logic. The model decouples the directional movement of the aircraft into a lateral equation of motion and a longitudinal equation of motion. The lateral control architecture utilizes the lateral equation of motion to control the aircraft in the lateral direction, while the longitudinal control architecture utilizes the longitudinal equation of motion to control the aircraft in the longitudinal direction. The initialization command logic selectively activates the lateral control architecture and the longitudinal control architecture. | 01-23-2014 |
20140025238 | System and Method for Multiple Aircraft Lifting a Common Payload - A system and method are provided for controlling a plurality of aircraft to lift a common payload. The system comprises of multiple aircraft tethered to a common payload, where the group of aircraft form a swarm that is controlled by a pilot station. Each aircraft is autonomously stabilized and guided through a swarm avionics unit, which further includes sensor, communication, and processing hardware. At the pilot station, a pilot remotely enters payload destinations, which is processed and communicated to each aircraft. The method for controlling a multi-aircraft lifting system includes of inputting the desired location of the payload, and determining a series of intermediary payload waypoints. Next, these payload waypoints are used by the swarm waypoint controller to generate individual waypoints for each aircraft. A flight controller for each aircraft moves the aircraft to these individual waypoints. | 01-23-2014 |
20140025239 | VEHICLE FEEDBACK - A feedback method and system. The method includes identifying by a computing system, a user. A vehicular feedback software application is enabled for the user. A feedback software application in the computing system monitors a group of vehicle operation functions currently being executed by the user with respect to a vehicle. The feedback software application analyzes the group of vehicle operation functions with respect to a profile associated with the user. An analysis report is generated in response to the analysis. The analysis report is presented to the user. The computing system monitors a response to the first analysis report from the user. | 01-23-2014 |
20140032016 | ADVANCED COOPERATIVE DEFENSIVE MILITARY TACTICS, ARMOR, AND SYSTEMS - This invention provides impact detection and vehicle cooperation to achieve particular goals and determine particular threat levels. For example, an impact/penetration sensing device may be provided on a soldier's clothing such that when this clothing is impacted/penetrated (e.g., penetrated to a particular extent) a medical unit (e.g., a doctor or medical chopper) may be autonomously, and immediately, provided with the soldiers location (e.g., via a GPS device on the soldier) and status (e.g., right lung may be punctured by small-arms fire). | 01-30-2014 |
20140032017 | INTEGRATED FRAMEWORK FOR VEHICLE OPERATOR ASSISTANCE BASED ON A TRAJECTORY PREDICTION AND THREAT ASSESSMENT - Various types and levels of operator assistance are performed within a unified, configurable framework. A model of the device with a model of the environment and the current state of the device and the environment are used to iteratively generate a sequence of optimal device control inputs that, when applied to a model of the device, generate an optimal device trajectory through a constraint-bounded corridor or region within the state space. This optimal trajectory and the sequence of device control inputs that generates it is used to generate a threat assessment metric. An appropriate type and level of operator assistance is generated based on this threat assessment. Operator assistance modes include warnings, decision support, operator feedback, vehicle stability control, and autonomous or semi-autonomous hazard avoidance. The responses generated by each assistance mode are mutually consistent because they are generated using the same optimal trajectory. | 01-30-2014 |
20140032018 | System and Method for Estimating States of Spacecraft in Planet-Moon Environment - A method estimates a state of a spacecraft in a planet-moon environment by executing iteratively a particle filter. The particle filter comprising integrates individually states of each particle of the particle filter according to a probability-evolution equation using a model of the state of the spacecraft represented as a planar circular restricted three-body problem and determines a prior probability of each particle as a previous posterior probability of a corresponding particle during a previous iteration. A joint probability distribution of the state of the spacecraft is determines using the states of each particle and the prior probabilities of each particle and the states and the prior probabilities of each particle are updated according to the joint probability distribution of the state of the spacecraft and a measurement of the state of the spacecraft to produce posterior probabilities of each particle. | 01-30-2014 |
20140032019 | Device and Method for Managing the Strategy to Join Waypoints - A device for managing strategies to join waypoints of a flight plan for a flight management system comprises: a typing module operating on an item of input data comprising an input waypoint with which is associated at least one operational requirement, for associating with the said item of data at least one typed waypoint comprising an output waypoint and an associated type, the type being determined from a database of types of waypoints, a module for determining strategy to join a typed waypoint, coupled with the typing module, for matching the said type with at least one associated joining strategy from a database of joining strategies. | 01-30-2014 |
20140032020 | GNSS OPTIMIZED CONTROL SYSTEM AND METHOD - A GNSS system in combination with a hydraulically-actuated, airborne dispenser for a dry material crop dusting system to optimize the distribution of dry materials over a particular tract of land. A GNSS subsystem is included using at least one GNSS antenna and one GNSS receiver located on the aircraft. The aircraft is equipped with an electronic/hydraulic crop dusting subsystem connected to a GNSS CPU. The GNSS ranging signals received by the antennas are processed by a receiver and processor system for determining the vehicle's position and dynamic attitude in three dimensions (3D). The system is adapted for operation in a differential GNSS (DGNSS) mode utilizing a base station at a fixed location. | 01-30-2014 |
20140032021 | SYSTEM AND METHOD FOR CONTROLLING AN UNMANNED AIR VEHICLE - A geodetic measuring system having a geodetic measuring unit having a beam source for emitting a substantially collimated optical beam. The measuring system also has an automotive, unmanned, controllable air vehicle having an optical module. An evaluation unit is also provided, wherein the evaluation unit is configured in such a manner that an actual state of the air vehicle, as determined by a position, an orientation and/or a change in position, can be determined in a coordinate system from interaction between the optical beam and the optical module. The measuring system has a control unit for controlling the air vehicle, wherein the control unit is configured in such a manner that control data can be produced using an algorithm on the basis of the actual state, which can be continuously determined in particular, and a defined desired state, and the air vehicle can be automatically changed to the desired state. | 01-30-2014 |
20140039729 | CUBESAT SYSTEM, METHOD AND APPARATUS - A satellite system includes a chassis, an avionics package included within an upper portion of the chassis. The avionics package includes a main system board, a payload interface board, at least one daughter board and a battery board. The main system board, the payload interface board, the at least one daughter board, and the battery board reside in substantially parallel planes. The payload interface board, the at least one daughter board, and the battery board are coupled to the main system board through one or more stackable connectors. A method of operating a satellite is also described. | 02-06-2014 |
20140039730 | SYSTEMS, METHODS, AND COMPUTER READABLE MEDIA FOR PROTECTING AN OPERATOR AGAINST GLARE - Systems, methods and computer readable media for protecting a pilot of an aircraft or an operator of a vehicle against glare from a luminous object. A system for attenuating glare experienced by an operator of a vehicle is provided with a transparent display unit or screen with adjustable pixels that is interposed between an operator of a vehicle and all or part of a windshield of the vehicle, and a device to control pixel intensity to attenuate glare from a luminous object. A system is provided with a positioning module for determining the position of the operator inside the vehicle, and for determining the position of at least one luminous object outside the vehicle that is a source of glare experienced by the operator. A system is provided with a computing device for computing a glare line between the operator and luminous object and the position of the display screen where the glare line intersects the display unit. | 02-06-2014 |
20140039731 | METHOD AND DEVICE FOR AIDING THE MANAGEMENT OF THE FLIGHT OF AN AIRCRAFT - The device comprises servocontrol means which automatically control, in a combined manner, an automatic thrust system of the aircraft and airbrakes of the aircraft, as a supplement to usual means for steering the vertical trajectory, so that the aircraft attains a speed setpoint and/or altitude setpoint, at the location defined by a geographical constraint. | 02-06-2014 |
20140039732 | Wind Calculation System Using a Constant Bank Angle Turn - A method and apparatus for operating an aircraft. The aircraft is flown at a constant bank angle in which the aircraft crosses an intended ground track for the aircraft. Information is identified about a wind using positions of the aircraft flying at the constant bank angle. | 02-06-2014 |
20140058591 | METHOD FOR PROVIDING FLIGHT DATA - A method of providing real-time flight data to an aircraft, which includes the flying of a first aircraft along a flight path and obtaining real-time flight data as the first aircraft is flown along the flight path. The method includes directly relaying at least a portion of the real-time flight data. | 02-27-2014 |
20140058592 | APPARATUS AND METHOD FOR FORECASTING GEOSTATIONARY SATELLITE ERROR - An apparatus and method for forecasting a geostationary satellite anomaly is provided. The method may include storing at least one piece of space environmental information, satellite information, and satellite anomaly event information, and estimating a satellite anomaly susceptibility to a space environmental phenomenon based on the at least one piece of space environmental information, the satellite information, and the anomaly event information. | 02-27-2014 |
20140067164 | METHODS AND APPARATUSES FOR AUTONOMOUS FLIGHT TERMINATION - Embodiments include a flight safety assembly onboard an aerial vehicle, which includes a first sensor configured to sense first information related to flight of the aerial vehicle and a second sensor configured to sense second information related to the flight of the aerial vehicle. A sensor input is adapted to receive third information related to the flight of the aerial vehicle. A processor is operably coupled to the first sensor, the second sensor, and the sensor input. The processor is configured to determine three independent instantaneous impact points for the aerial vehicle by independently analyzing each of the first information, the second information and the third information. The processor is also configured to generate three independent onboard flight termination indicators for each of the three independent instantaneous impact points that intersects with a region to be protected. | 03-06-2014 |
20140067165 | SYSTEM AND METHOD FOR UTILIZING MULTIPLE SENSORS - A sensor system having multiple sensors and having a grid generator projecting into space a relative navigation grid and a method of utilizing multiple airborne sensors operably coupled to an aircraft and coordinating the sensor outputs from the airborne sensors based on the determined spatial position of the multiple sensors and a method for utilizing multiple airborne sensors. | 03-06-2014 |
20140067166 | METHOD OF CONTROLLING AN ELECTRIC PROPULSION SYSTEM - An apparatus is described comprising: at least one processor; and memory storing instructions that, when executed by the at least one processor, cause the apparatus to: regulate an operation of a motor based at least in part on a control imposed on an output torque of the motor and a rate of change of a speed of the motor. | 03-06-2014 |
20140067167 | UNMANNED DEVICE INTERACTION METHODS AND SYSTEMS - Structures and protocols are presented for configuring an unmanned aerial device to participate in the performance of tasks, for using data resulting from such a configuration or performance, or for facilitating other interactions with such devices. | 03-06-2014 |
20140067168 | Horizontal Tail Load Alleviation System - A method for controlling control surfaces. A position limit is identified for movement of a control surface based on a load limit set for the control surface and a number of vehicle current operation parameters to form an identified position limit. Responsive to receiving a command to move the control surface on a vehicle to a new position, the control surface is commanded to move to a position within the identified position limit. | 03-06-2014 |
20140067169 | ELECTRIC TAXI AUTO-GUIDANCE AND CONTROL SYSTEM - An auto-guidance and control method and system are provided for use in conjunction with an aircraft electric taxi system, wherein electric taxi guidance may be performed in a manual mode by a crew or in an auto-mode by an auto-guidance and control system. First, aircraft status data and airport feature data are accessed. A processor, in response to at least the aircraft status data and the airport feature data, generates taxi guidance information and renders the taxi guidance information on a display. A guidance route is manually navigated utilizing guidance information on the display in the manual mode. In the auto mode, taxi-path commands, generated by the processor, are applied to taxi path guidance controllers in the auto-mode. | 03-06-2014 |
20140074321 | METHODS AND SYSTEMS FOR VEHICLE BROADBAND CONNECTION TO A DATA NETWORK - Methods and systems for communicating data between a vehicle and a ground-based unit are provided. The method includes communicatively coupling the vehicle to the ground-based unit, initiating a Broadband over Power Line (BPL) link between the vehicle and the ground-based unit when power is supplied to the vehicle, and updating data stored in the vehicle with data received from the ground-based unit. | 03-13-2014 |
20140074322 | AIRCRAFT AVIONICS TABLET INTERFACE MODULE - An aircraft avionics system including an aircraft interface device configured to communicate with an aircraft avionics system and a tablet interface module configured to communicate with the aircraft interface device and with one or more tablets. The aircraft avionics system includes a plurality of sensors for an aircraft and the tablet interface module provides the one or more tablets with information received from the aircraft interface device. | 03-13-2014 |
20140074323 | METHOD FOR MODIFYING AN AIRCRAFT FLIGHT PLAN ON A TOUCH-SENSITIVE SCREEN - The general area of the invention is that of methods for managing flight plans by an avionic system comprising a visualization device and a touch-sensitive interface. The visualization device displays a cartographic representation of the terrain flown over, aeronautical data and a flight plan composed of a set of segments connecting together certain aeronautical waypoints. The management method contains several steps, a first editing step activated by touch-sensitive designating of any point of the flight plan, a second modification of the flight plan step activated by a touch-sensitive movement, the end of the touch-sensitive movement triggering a movement or an addition or the removal of a waypoint. The method also makes it possible to easily manage the airways in order to incorporate them into a flight plan during modification. | 03-13-2014 |
20140081482 | METHOD AND DEVICE FOR AUTOMATICALLY MANAGING THE SPACING OF AT LEAST ONE FOLLOWING AIRCRAFT BEHIND AT LEAST ONE TARGET AIRCRAFT - The system ( | 03-20-2014 |
20140088799 | SYSTEMS AND METHODS PROVIDING A FUEL-EFFICIENT RTA IMPLEMENTATION WITH UNCERTAIN WINDS - Flight management systems and control methods for meeting a required time of arrival (RTA) with reduced fuel burn. The method can account for probabilistic wind forecast uncertainty in RTA calculations by reformulating the speed and thrust profile problem as a multi-stage stochastic program, using a wind forecast uncertainty model to generate scenario sets for the fuel optimization problem. The method can iteratively calculate a fuel-efficient advised air speed for achieving an RTA over a flight path with an arbitrary number of recourse points. | 03-27-2014 |
20140095001 | ALTITUDE AND ACCELERATION COMMAND ALTITUDE HOLD ALGORITHM FOR ROTORCRAFT WITH LARGE CENTER OF GRAVITY RANGE - A flight control system includes an Acceleration and Attitude Command/Velocity Hold mode (AACVH) algorithm which blends attitude commands with acceleration commands This blending determines a trim attitude for a given rotorcraft flight condition. | 04-03-2014 |
20140100718 | FLIGHT CONTROL SYSTEM USING SIMPLEX COMPUTERS AND AIRCRAFT COMPRISING SAME - A system for computing flight commands, which comprises simplex computers coupled to form virtual command/monitor pairs. These virtual pairs send the commands computed to actuators whose controller implements an election of the pair whose command will be taken into account by the actuator. | 04-10-2014 |
20140100719 | ELECTROMECHANICAL BRAKING SYSTEM ARCHITECTURE - The invention relates to a braking system architecture for an aircraft having wheels 1 braked by means of respective brakes 2, each brake having a plurality of electromechanical actuators | 04-10-2014 |
20140107871 | Turbulence Mitigation for Touch Screen Systems - A method and apparatus for managing a touch screen system. Data generated by an acceleration detector about acceleration of the touch screen system is received. The acceleration detector is located within the touch screen system. An action is initiated by an input manager when the acceleration of the touch screen system reduces usability of the touch screen system. | 04-17-2014 |
20140114505 | Yaw Damping System And Method For Aircraft - An alternative system for damping the dutch roll mode in an aircraft is provided using roll control surfaces. Classical yaw dampers for the dutch roll mode utilize the yaw control surfaces such as a rudder to dampen the dutch roll mode oscillations. An alternative damper is described that utilizes roll control surfaces such as spoilers or ailerons to dampen the dutch roll mode. | 04-24-2014 |
20140121861 | CONFIGURABLE AIRCRAFT DATA ACQUISITION AND/OR TRANSMISSION SYSTEM - An aircraft data acquisition and/or transmission system comprises a memory having stored therein a first state machine configuration comprising a first allocation between a plurality of transition criteria objects stored in a first area of the memory and a plurality of state objects stored in a second area of the memory separate from the first area. A processor is coupled to the memory and at least one application executable by the processor causes a first data acquisition and/or transmission behavior in the aircraft by running the first state machine configuration, receives a second state machine configuration comprising a second allocation between the plurality of transition criteria objects and the plurality of state objects, and causes a second data acquisition and/or transmission behavior in the aircraft by running the second state machine configuration. | 05-01-2014 |
20140121862 | CONSOLIDATED VEHICLE PROPULSION CONTROL USING INTEGRATED MODULAR AVIONICS - A vehicle is provided. The vehicle may include, but is not limited to, a virtual backplane, a vehicle management computer communicatively coupled to the first virtual backplane and having a first predetermined schedule, a consolidated propulsion controller communicatively coupled to the virtual backplane and having a second predetermined schedule different from the first predetermined schedule, at least one engine communicatively coupled to the first virtual backplane, each of the at least one engines having a unique schedule, and at least one control system communicatively coupled to the first virtual backplane, each of the at least one control systems having a unique schedule, wherein each of the vehicle management computer, consolidated propulsion controller, at least one engines and at least one control system are configured to add and consume date from the virtual backplane according to their respective schedules. | 05-01-2014 |
20140129055 | Unpredictable Vehicle Navigation - A system and method for controlling movement of a vehicle. A current state of the vehicle is identified. The current state comprises a current location of the vehicle. A next state for the vehicle is selected by a processor unit. The next state comprises a next location for the vehicle. A value for an attribute of the next state of the vehicle is randomly selected. The movement of the vehicle is controlled to move the vehicle from the current state to the next state. | 05-08-2014 |
20140136026 | BRAKING CONTROL SYSTEM AND METHOD - A control system and method of the anti-skid computers of an aircraft are provided. The control system comprises two IMA computers, comprising each one an Avionics Computer Control Device, an Avionics Computer Monitoring Device and at least one dual data acquisition means and at least one dual processing means. Each Avionics Computer Control Device and each Avionics Computer Monitoring Device are connected to the anti-skid computers of both sides. | 05-15-2014 |
20140136027 | MANAGEMENT SYSTEM FOR AIRCRAFT - Said system ( | 05-15-2014 |
20140136028 | Avionics Method and Apparatus - The present invention comprises methods and apparatuses for sensing attributes of an aircraft and efficiently communicating relevant attributes to a pilot. The invention allows a state of the aircraft to be determined, and then used to control systems, configure displays, select checklists relevant to the determined state, and automatically respond to emergencies based on the aircraft state. Embodiments of the invention can use the determined state of the aircraft to monitor and control electrical sensors and system as appropriate for the determined state; to communication information relevant to the determined state to a pilot (e.g., by displaying gauges in a manner and priority specific to the determined state); and to display contextually-relevant checklists (e.g., displaying a checklist of actions necessary for an aircraft in the determined state). | 05-15-2014 |
20140136029 | FLIGHT CONTROL DEVICE, SPACECRAFT, AND REFERENCE TRAJECTORY CORRECTING METHOD - A flight control method and device for correcting a reference trajectory based on a distance from a current position to a target position in a spacecraft in flight. A CPU included in the spacecraft generates a reference trajectory which is a trajectory for allowing the spacecraft in flight to arrive at the target position on a celestial body with the atmosphere, and which is identified based on velocity or energy of the spacecraft and on drag acceleration of the spacecraft. The CPU calculates a ratio between the range that is a distance from the current position based on the reference trajectory to the target position, and the real range that is a real distance from a current position to the target position, and corrects the reference trajectory by calculating the drag acceleration in the reference trajectory using the calculated ratio. | 05-15-2014 |
20140136030 | METHOD FOR INTEGRATING ENGINE CONTROL AND FLIGHT CONTROL SYSTEM - A method of operating an aircraft system includes receiving flight information and trajectory intent information other than current values by an engine control system associated with an engine of the aircraft system from a flight control system associated with the aircraft system; and operating an engine associated with the engine control system using the received non-current information. An aircraft includes an engine positioned on the aircraft; a full authority digital engine controller (FADEC) communicatively coupled to the engine; and a flight control system positioned on the aircraft and communicatively coupled to the FADEC, the flight control system configured to transmit other than current values of flight information and trajectory intent information to the FADEC and to receive other than current values of at least one of engine health and parameters used to estimate engine health from at least one of the FADEC and a separate flight control center positioned offboard the aircraft. | 05-15-2014 |
20140142787 | Determination of Flight Path for Unmanned Aircraft in Event of In-Flight Contingency - An enhanced control system for an unmanned aerial vehicle adds constraints to the process of choosing a flight path in the event of an in-flight contingency, such as engine out or an encounter with jamming, which forces a diversion or unplanned landing. The constraints are: (1) ensure communications are available when needed during contingency operations; and (2) ensure signals from a global positioning system (or other navigation system) are available when needed during contingency operations. | 05-22-2014 |
20140142788 | SYSTEM AND METHOD FOR PROVIDING ACCURACY IN AIRDROP MISSIONS - System and method for aiding the accuracy of airdrop missions by performing localized weather data collection in a column of air and then subsequently storing, decimating and forwarding the data to a remote location. A first aircraft flies to the geographic location of the desired airdrop, deploys an atmospheric conditions sensing dropsonde, collects the data from the dropsonde, stores that data, then transmits that data or a decimated subset of that data either once or any number of consecutive times, to a second aircraft located at a predetermined distance from the first aircraft. | 05-22-2014 |
20140142789 | Unknown - An onboard flight management system in an aircraft comprises means for continuously calculating first geolocation data, from data received from at least one external geolocation device, comprising a current position and future positions of an aircraft along a trajectory sequenced in several portions and comprising second data comprising demands required by an international navigation procedure called “Required Navigation Performance”, or RNP, for all the portions of the trajectory. The management system additionally comprises a means for displaying first and second data all the way along the trajectory, the first and second data being represented graphically and simultaneously on the said display means in order to enable the pilot to anticipate the flight characteristics for the aircraft and make them converge toward the required demands of the next trajectory portion. | 05-22-2014 |
20140148977 | LAPTOP BASED RAPID CONTROL LAWS DEVELOPMENT - A system and method to modify a qualified actuator command with an unqualified actuator command modifier. The method includes creating a modified actuator command as the difference between the qualified actuator command and the unqualified actuator command and thereafter limiting the modified actuator command with an authority limiter. The system includes a qualified computer having an unqualified control law interfaced with an unqualified computer having a qualified control law. | 05-29-2014 |
20140148978 | METHODS AND SYSTEMS FOR DIRECTING BIRDS AWAY FROM EQUIPMENT - A system for directing a bird away from equipment includes an item of equipment and a detector configured to detect a bird that could be harmed by or that could harm the equipment and to determine the proximity of the bird to the equipment. The system also includes an unmanned aerial vehicle and a pilot system configured to control the unmanned aerial vehicle. | 05-29-2014 |
20140148979 | NAVIGATION PERFORMANCE SPECIFICATION - A method of formulating a specification for temporal and vertical required navigation performance is disclosed. The method assesses various flight management guidance systems methods and allows a specification to be set for an airport. The specification may be used to increase aircraft traffic into the airport. The specification sets limits on deviations in time and altitude, for example, on approach into arrivals at the airport. The method comprises: calculating temporal and vertical deviations from a reference trajectory for one or more flight management guidance methods for one or more aircraft types; and comparing the temporal and vertical deviations with operational requirements of the airport. The deviations from a reference trajectory may result from uncertainties affecting trajectory prediction, such as wind and temperature prediction accuracy. | 05-29-2014 |
20140156113 | METHOD OF MANAGING A STEERING COMMAND FOR A STEERABLE PORTION OF AIRCRAFT LANDING GEAR - The invention relates to a method of managing a steering command for a steerable portion | 06-05-2014 |
20140156114 | METHOD FOR DISPLAYING AN AERONAUTICAL FLIGHT PLAN COMPRISING A STEP OF FLIGHT DATA CONFIGURATION - The general field of the invention is that of methods of graphic representation, modification and validation of an aeronautical flight plan for an aircraft avionics system. The system comprises means for computing and generating said flight plan, a task management system, a visualization device displaying a graphic representation of said flight plan and a man-machine interface suitable for making selections, modifications or additions to the information contained in said graphic representation, said selections, modifications and additions being taken into account by the task management system, said graphic representation containing a timeline on which feature at least the various phases of the flight plan and the information corresponding to said phases. The method according to the invention contains a step of displaying at least one item of information depending on several parameters and the graphic representation of which depends on the level of available information about said parameters. | 06-05-2014 |
20140156115 | METHOD FOR DISPLAYING AN AERONAUTICAL FLIGHT PLAN COMPRISING A STEP OF DISPLAYING AND SELECTING THE TASKS TO BE ACCOMPLISHED BEFORE A CHANGE OF FLIGHT PHASE - The general field of the invention is that of methods of graphical representation, modification and validation of an aeronautical flight plan for an aircraft avionics system. Said system comprises means for computing said flight plan, a system for managing the tasks necessary for the accomplishment of said flight plan, a visualization device displaying a graphical representation of said flight plan and a man-machine interface able to carry out selections, modifications or additions in the information contained in said graphical representation, said selections, modifications and additions being taken into account by the task management system. The graphical representation comprises a timeline on which feature at least the various phases of the flight plan and the corresponding information. The method comprises a step of displaying at least one first interactive graphical icon, representative of the overall state of progress of the tasks to be performed before a change of flight phase. | 06-05-2014 |
20140163781 | Tree Metrology System - A method and apparatus for identifying a number of diameters for a group of trees. An unmanned aerial vehicle moves on a route through the group of trees at a height that is configured to allow measurement of the number of diameters for the group of trees by a sensor system associated with the unmanned aerial vehicle. Information is generated about the number of diameters for the group of trees using the sensor system associated with the unmanned aerial vehicle. | 06-12-2014 |
20140163782 | Aircraft data management system - An aircraft data management system comprises a first storage device for data representative of operating parameters of the aircraft, the first device being situated on the ground, and second storage device for data representative of parameters of said aircraft, the second device being embedded onboard said aircraft. The system also comprises a device for accessing the data contained in said first and second storage devices. The system also comprises a device for determining the stopping of the aircraft on the ground, a device for synchronizing the data contained in the first and second storage devices, according to information from the determination device. Furthermore, the access device also being designed to select the first or the second storage device to access the data, according to the information from the determination device authenticate a user accessing the data. | 06-12-2014 |
20140172200 | UNMANNED AERIAL VEHICLE ANGULAR REORIENTATION - A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value. | 06-19-2014 |
20140172201 | METHOD FOR MONITORING THE LOCKING MEANS OF AN ELECTRICAL THRUST REVERSAL SYSTEM FOR A TURBINE ENGINE - A method for monitoring at least one locking device of an electrical thrust reversal system for a turbine engine, the method being carried out by a computer prior to the take-off of the turbine engine, the method including sending a command for opening the locking devices; verifying the opening of the locking devices; sending a command for closing the locking devices; and verifying the closing of the locking devices. | 06-19-2014 |
20140180502 | SITUATION AFTERMATH MANAGEMENT SYSTEM AND METHOD - A system and method for assisting flight crew recovery in the aftermath of an unexpected event is provided. A processor is used to detect that an unexpected event has occurred in an aircraft and, in response to detecting that the unexpected event has occurred, state data are stored in memory. The processor is also used to detect that the expected event has been resolved and, in response to detecting that the unexpected event has been resolved, the processor retrieves the state data from the memory, generates an aftermath plan that includes prompts to guide the flight crew to complete the aftermath plan, and continuously updates the aftermath plan until the aftermath plan is completed. | 06-26-2014 |
20140180503 | SYSTEM FOR PROVIDING INDEPENDENT AND DISSIMILAR FLIGHT PARAMETER ESTIMATES OF AN AIRCRAFT AND ASSOCIATED AIRCRAFT - The invention relates to a system for estimating flight parameters of an aircraft, having a plurality of static pressure ports and a plurality of measuring probes, each measuring probe having an aerial portion and an electronic device configured to estimate the flight parameters. A first and second measuring probe have identical aerial portions and identical electronic devices, a third measuring probe has an aerial portion and an electronic device that are different from those of the first measuring probe; the electronic devices of the first, second and third measuring probes and the static pressure ports are connected so as to form a first, second and a third data system respectively associated with a static pressure port, and each static pressure port of each of the data systems is separate from each static pressure port of the other data systems. | 06-26-2014 |
20140180504 | AIRCRAFT CONTROL SYSTEM WITH MERGED LINKS - The invention relates to an aircraft control system, situated in the avionics bay, including a computer, a remote equipment, such as an actuator of control surfaces, and an AFDX network. The computer includes a first module and a second module, respectively connected to a corresponding first module and a second module of the equipment, by a first and a second virtual link sharing a common path through the network, the first and second virtual links being segregated by a separate encoding at the applicative level. A replication and/or frame switching device is connected, on the one hand, to the common port and, on the other hand, to the ports of the first and second modules of the equipment. | 06-26-2014 |
20140180505 | METHOD OF MANAGING THE BRAKING OF AN AIRCRAFT - The invention relates to a method of managing the braking of an aircraft, the aircraft having a plurality of wheels R | 06-26-2014 |
20140180506 | METHOD OF MANAGING THE BRAKING OF AN AIRCRAFT - A method of managing the braking of an aircraft, the aircraft having a plurality of wheels R | 06-26-2014 |
20140180507 | Hybrid architecture for an aircraft system - A method of configuring an aircraft management system comprising the following steps, implemented by a configuration module integrated into the avionic system of the aircraft cockpit: obtaining at least one item of computation data for computing at least one configuration parameter of the management system, sending, to a computation module that is independent from the avionic system of the aircraft cockpit, a request for computing said at least one parameter on the basis of said at least one item of computation data, receiving, from said computation module, said at least one computed parameter, and configuring said management system with said at least one received computed parameter. | 06-26-2014 |
20140188311 | ELECTRONIC KIT BAG - The Electronic Kit Bag (EKB) is a computerized, portable pilot “kit bag” that accepts input data, manipulates said data, and outputs solutions. The EKB consists of standard and state-of-the-art computing parts and peripherals, interfaced for maximum utility. The central operating program of the device assesses the relationships of input data through a logic based, three-dimensional decision-making algorithm. Data output is utilized either directly by the user, by the user through an aircraft system, or directly from the EKB to an aircraft system or autopilot. | 07-03-2014 |
20140188312 | METHODS, SYSTEMS, AND APPARATUS FOR LAYERED AND MULTI-INDEXED FLIGHT MANAGEMENT INTERFACE - Methods, systems, and apparatus for tab-pane-based flight plan management interface are disclosed. The tab-pane-based flight management interface system (FMIS) is optimally Layered and Multi-Indexed (LMI) such that the management of flight management (FM) functions and associated parameters that affect the airplane's flight are easily and efficiently operable by pilots. The LMI-FMIS provides a flexible tab-pane-based architecture that allows pilots to start a flight plan modification, proceed to engage in other tasks not related to the modification, and return to the pending modification to continue the modification process. The LMI-FMIS also provides task-oriented menu structures that provide pilots tailored options or menus applicable to the task at hand thus efficiently guiding pilots to complete a task while maintaining easy access to information that was displayed prior to the commencement of the task. | 07-03-2014 |
20140200746 | Aircraft Health Assessment System - According to one embodiment, a system for assessing health of an aircraft includes a receiver, a flight spectrum analyzer, and a health assessment analyzer. The receiver receives, from an aircraft, a plurality of measurements associated with two or more flight parameters. The plurality of measurements includes measurements spanning at least one period of time. The flight spectrum analyzer determines, based on a comparison of the plurality of measurements to a plurality of flight spectrum definitions, an amount of time the aircraft spent in each flight spectrum of a plurality of flight spectrums during the at least one period of time. The health assessment analyzer assesses a change in health of the aircraft over the at least one period of time based on the determination of the amount of time the aircraft spent in each flight spectrum and a plurality of spectrum health profiles. | 07-17-2014 |
20140200747 | METHOD, DEVICE, AND COMPUTER REDABLE MEDIA FOR AUTOMATIC MANAGEMENT OF CONFIGURATION AND RECONFIGURATION OF A PLURALITY OF SYSTEMS OF AN AIRCRAFT - Methods, devices, and computer readable media are disclosed for automatic management of configuration and reconfiguration procedures of a plurality of systems of an aircraft, for example and without limitation, for aircraft operational and maintenance uses. In some aspects, a centralized device for automatic management of configuration and reconfiguration procedures of a plurality of systems of an aircraft includes a central unit for automatically generation control commands for automatic control of at least one action to be executed for one or both of the configuration or reconfiguration procedure, data links for automatic dispatch of control commands to corresponding systems for automatic execution. | 07-17-2014 |
20140200748 | SYSTEMS FOR TASKS GUIDANCE OF OPERATIONS MANAGEMENT IN AN AIRCRAFT COCKPIT - Aircraft guidance assistance systems and computer readable media are disclosed. The present subject matter includes systems and computer readable media for providing task guidance for managing flight operations during normal operating procedures or exceptional situations caused by abnormal events. In some aspects, a system for providing task guidance can include a processor, memory, and a flight assistance module configured to receive data from multiple servers. The assistance module can display possible aircraft flight phases while indicating the flight phase. The assistance module can also display operations to be carried out for the flight phases, and the actions corresponding to these operations. | 07-17-2014 |
20140200749 | UNMANNED AIR VEHICLE COMMUNICATIONS - A communications management system, including a configurable router, and method, for an unmanned air vehicle (UAV), arranged to selectively route data between a plurality of avionic subsystems/communications resources on the UAV and a plurality of transceivers on the UAV, the routes selected being determined at least in part according to a desired red and black data separation of data to be transmitted from the transceivers and/or a red and black data separation of data being received by the transceivers. | 07-17-2014 |
20140200750 | System for piloting an aircraft provided with a performance functions server - A piloting system including a performance functions server which is linked to all the computers of the piloting system, which hosts all the performance functions of the piloting system and which is able to supply the results of performance functions to at least said computers of the piloting system. | 07-17-2014 |
20140200751 | FLIGHT RECORDING SYSTEM IN AN AIRCRAFT INTEGRATING THE AUDIO MANAGEMENT FUNCTION - A flight recording system with a simple, precise, reliable and low cost installation and connection architecture. This system includes a box provided with reversible fastening means onto the aircraft, said box comprising recording means for recording conversations and audio communications and audio management means for managing signals and for providing the recording means with signals originating from the audio environment of the cockpit. | 07-17-2014 |
20140214243 | FORMATION FLIGHT CONTROL - An apparatus for controlling the formation flight of a trailing aircraft relative to a vortex generated by a leading aircraft includes a position module, peak-seeking module, limiter module, and control module. The position module is configured to determine a position of the vortex relative to the trailing aircraft. The peak-seeking module is configured to determine a desired position of the trailing aircraft for providing desired vortex-induced aerodynamic benefits based on the position of the vortex relative to the trailing aircraft and a mapping function of an individual performance metric. The limiter module is configured to modify the desired position of the trailing aircraft to avoid unintended crossings of the trailing aircraft into the vortex. Finally, the control module is configured to control flight of the trailing aircraft based on one of the desired position of the trailing aircraft and modified desired position of the trailing aircraft. | 07-31-2014 |
20140214244 | ELECTRONIC BOARD FOR AVIONICS EQUIPMENT COMPRISING VIBRATION DAMPING MEANS BETWEEN ITS REINFORCING SURROUND AND ITS RETENTION MEANS - An electronic board for avionics equipment, the board comprising a printed circuit, a reinforcing surround and board retention means. In order to improve the vibration resistance of the board, the board further comprises vibration damping means interposed between the reinforcing surround and the retention means. | 07-31-2014 |
20140222254 | METHOD AND APPARATUS FOR A PASSIVE AVIONICS DATA TRANSFER DEVICE FOR USE WITH COTS TABLET EQUIPMENT DEPLOYED AS CLASS I OR II ELECTRONIC FLIGHT BAG SYSTEMS - The present disclosure provides an aerospace grade data conversion apparatus. The data conversion apparatus includes an avionics interface module for: collecting data outputs from a plurality of analog and digital avionics and electrical data sources; aligning digital data respectively output from the plurality of digital data sources; and commingling the digital data in order to generate a data sequence interpreted by a receiving device, the receiving device including an electronic tablet. The present disclosure also provides a software developer's kit. The software developer's kit includes a library configured to allow application software developers to utilize digital data output from an avionics interface module. The present disclosure further includes a mounting system. The mounting system includes one or more assemblies for securing an electronic flight bag device to an aircraft, wherein the electronic flight bag includes an electronic tablet. | 08-07-2014 |
20140222255 | APPARATUS AND METHOD FOR MONITORING STATUS OF SATELLITE - Provided is an apparatus and method for monitoring a status of a satellite, including classifying satellite telemetry information and space weather information and storing the information in a storage unit including respective databases, predicting whether a predetermined type of satellite failure occurs based on the space weather information, and generating satellite control command information to change a status of a predetermined satellite configuration when a satellite failure determining index used to determine a possibility of the satellite failure is beyond a predetermined critical alert range. | 08-07-2014 |
20140236394 | METHODS AND SYSTEMS FOR AIRCRAFT DATA COMMUNICATIONS OVER HETEROGENEOUS CONNECTIVITY - Methods and systems for communicating data between an aircraft and an off-board network are provided. The method includes pre-loading data for the aircraft onto a secure power unit, communicatively coupling the aircraft to the secure power unit, validating the aircraft at the secure power unit based on air traffic management information, absolute (GMT) time, and aircraft location data, and transferring data between the aircraft and the secure power unit based on the validation. | 08-21-2014 |
20140236395 | DEVICE FOR MAKING AVAILABLE NAVIGATION PARAMETER VALUES OF A VEHICLE - A device for making available navigation parameter values of a vehicle is provided. The device includes components distributed in the following categories: several sensors collecting measurement data relating to at least one navigation parameter of the vehicle; several computers processing the measurement data collected by the sensors and calculating said navigation parameters; several networks linking the sensors to the computers and linking the computers to systems using said parameters. The networks transmit all the collected measurement data to the computers, which calculate a value for each navigation parameter as well as an estimated value of the associated fault, using a single common fusion algorithm. | 08-21-2014 |
20140236396 | METHOD AND SYSTEM FOR DETECTING JAMMING AND/OR UNCONTROLLED MOVEMENT OF AN AIRCRAFT CONTROL SURFACE - A system for detecting jamming and/or uncontrolled movement of an aircraft control surface includes first means for estimating the value of at least one parameter of an equation simulating the feedback loop dynamic of the control surface, according to a recursive autoregressive method with exogenous variable of RARX type in a recursive least squares way, and second means for detecting jamming and/or uncontrolled movement of the control surface, according to the estimated parameter value by the application of a decision test in the parametric space. | 08-21-2014 |
20140236397 | SYSTEMS AND METHODS PROVIDING A FUEL-EFFICIENT RTA IMPLEMENTATION WITH UNCERTAIN WINDS - Flight management systems and control methods for meeting a required time of arrival (RTA) with reduced fuel burn. An example method can account for probabilistic wind forecast uncertainty in RTA calculations by reformulating the speed and thrust profile problem as a multi-stage stochastic program, using a wind forecast uncertainty model to generate scenario sets for the fuel optimization problem. The method can iteratively calculate a fuel-efficient advised air speed for achieving an RTA over a flight path with an arbitrary number of recourse points. | 08-21-2014 |
20140244075 | DAMAGE ADAPTIVE CONTROL - Embodiments of the disclosure are directed to measuring, via at least one sensor, at least one of a damage and a compromise associated with a vehicle, determining at least one of a region and a location of the at least one of a damage and a compromise and a level of the at least one of a damage and a compromise, and adapting an operational envelope for the vehicle based on the determined at least one of a region and a location of the at least one of a damage and a compromise and the level of the at least one of a damage and a compromise. | 08-28-2014 |
20140244076 | STABILITY BASED TAXIING AND TURNING METHOD FOR AIRCRAFT WITH ELECTRIC TAXI SYSTEM - Landing gear apparatus for an aircraft may include a steerable nosewheel assembly and left main landing gear wheels and right main landing gear wheels driven by motors. A controller may receive an angular position of the nosegear wheel assembly. The controller may respond to the angular position by transmitting wheel speed signals to one or more of the motors to maintain the center of gravity of the aircraft within a predetermined stability triangle and to perform short radii turning. | 08-28-2014 |
20140257597 | INTERFACE SYSTEM FOR MULTIPLE PROTOCOLS - An interface system for a plurality of different protocols. The system includes a single receiver, a processor and a single transmitter. The receiver may convert an input signal to a 1/0 signal according to a determined one of the plurality of different protocols. The processor may receive the converted logic level signal and parse the converted logic level signal into data according to the determined one protocol. The transmitter may receive the translated signal and convert the translated signal to an output signal having a format readable by an external device. | 09-11-2014 |
20140257598 | Real-Time Adaptive Speed Scheduler - A real-time adaptive speed scheduler that optimizes the control of an aircraft's speed and speed mode through the introduction of an advisory providing an optimized speed schedule for improved fuel efficiency and aircraft predictability. This system can also be deployed to improve flight efficiency and aircraft predictability in situations where time needs to be gained or lost, or air traffic needs to be sequenced. The real-time adaptive speed scheduler disclosed herein provides a datalink solution for loading directly into an aircraft's flight management system, for operation and display on a mobile device, as an advisory to an air traffic controller for instruction to the aircraft as a voice command, any authorized subscriber, and/or as an advisory to a dispatcher at an airline operations center. | 09-11-2014 |
20140257599 | ELECTRIC PROPULSION SYSTEM CONTROL APPARATUS - The present invention provides an electric propulsion system control apparatus that uses electric means alone so that effects pertaining to weight and cost are suppressed, is capable of accurate detection even when an airspeed has a binary relationship with a torque and a rotation speed of a propeller, and thereby exhibits improved detection precision and responsiveness. The electric propulsion system control apparatus drives a propulsion propeller to rotate, and is configured to estimate the airspeed from a data set stored in advance in relation to the airspeed and a propeller characteristic, and a plurality of torque and rotation speed estimation values detected under different driving conditions. | 09-11-2014 |
20140257600 | APPARATUS FOR CONTROLLING A PLURALITY OF APPLIANCES ABOARD A VEHICLE - An apparatus for controlling appliances aboard a vehicle, including a first data processing device having a network interface that can have a vehicle network for bidirectional data transmission between the first data processing device and connected network appliances. Also provided are an input/output device, a graphics processor device connected to the screen thereof and to the first data processing device, a user interface module provided in the first data processing device and that implements a graphical user interface having pages, and at least one separate second data processing device connected to the first data processing device via a separate bidirectional data link and having a network interface for connection to a vehicle network. Via each bidirectional data link it is exclusively possible to transmit predefined data records having data of predefined data types for display on pages from the second data processing device to the first data processing device. | 09-11-2014 |
20140277853 | SYSTEM AND METHOD FOR DETERMINING AIRCRAFT OPERATIONAL PARAMETERS AND ENHANCING AIRCRAFT OPERATION - A method for identifying variations in aircraft operational parameters includes processing a four-dimensional (4D) aircraft trajectory for a flight along a defined route. The method also includes determining an aircraft intent corresponding to the flight along the defined route based at least in part on an aircraft performance model from a trajectory predictor. The aircraft intent includes multiple segments and corresponding intent parameters. In addition, the method includes adjusting the intent parameters such that a computed 4D trajectory substantially corresponds to the 4D aircraft trajectory. The method further includes determining a computed operational parameter based at least in part on the computed 4D trajectory and the aircraft performance model from the trajectory predictor. In addition, the method includes identifying variations between the computed operational parameter and a corresponding measured operational parameter. | 09-18-2014 |
20140277854 | MODULAR DRONE AND METHODS FOR USE - Various exemplary embodiments relate to a drone. The drone may include: a navigation unit configured to determine the location of the drone and navigate the drone to designated locations; a radio frequency identification (RFID) reader configured to read RFID tag information from RFID tags; and a wireless network transceiver configured to periodically transmit the location of the drone and RFID tag information to an inventory management system. Various exemplary embodiments relate to a method performed by a drone. The method may include: receiving navigation path information; navigating the drone along the navigation path based on satellite location signals; determining current position information based on the satellite location signals; reading RFID tag information from a first RFID tag; and transmitting the RFID tag information and the current position information via a wireless client to a central computing system. | 09-18-2014 |
20140277855 | COMPENSATING FOR LEAD-LAG IN ROTOR SYSTEM - A control system for a rotor assembly includes a plurality of sensors configured to detect a lead-lag rate of each rotor blade of a plurality of rotor blades rotatable around a shaft and a flight control computer configured to generate lead-lag compensation signals based on the detected lead rate and lag rate of each rotor blade to control each rotor blade. | 09-18-2014 |
20140288730 | Method of Flying an Unmanned Aerial Vehicle - A method of flying an unmanned aerial vehicle (UAV) in response to emergency conditions, the method including steps implemented using a controller forming part of the unmanned aerial vehicle, said steps comprising: defining a plurality of emergency conditions; associating each emergency condition with a priority level; associating each emergency condition with an objective; sensing a plurality of operating parameters of the unmanned aerial vehicle to detect whether one of the plurality of emergency conditions exists; when one or more emergency condition is detected: generating a trajectory for the detected emergency condition having a highest associated priority level, wherein the trajectory is generated in accordance with the objective associated with the emergency condition that has the highest associated priority level; and instructing the unmanned aerial vehicle to follow the generated trajectory. | 09-25-2014 |
20140288731 | Flight Control System - A system and method for a controlling an aircraft with flight control surfaces that are controlled both manually and by a computing device is disclosed. The present invention improves overall flight control operation by reducing the mechanical flight control surface components while providing sufficient back-up control capability in the event of either a mechanical or power-related failure. Through the present invention, natural feedback is provided to the operator from the mechanical flight control surface which operates independent of computer-aided flight control surfaces. Further, through the present invention, force input signals received from the pilot are filtered to improve the operation of the computer-aided flight control surfaces. | 09-25-2014 |
20140303812 | BACKUP CONTROL SYSTEM - An aircraft control system includes an effector module connected to a control input and a primary control module connected to the effector module. A microprocessor in the effector module provides a backup control path bypassing the primary control module when the primary control module is in a failed state. | 10-09-2014 |
20140303813 | Aircraft Avionics Management and Control System - The disclosure describes an aircraft avionics management and control system, including apparatuses and methods, for consolidating aircraft avionics management and control operations and for allowing universal management, control, and operation of a plurality of communications systems, navigation systems, transponder systems, and other avionics systems with a single device. The communication systems may comprise a plurality of military radios, civilian radios, or other communication systems of different types and may have different manufacturers. Similarly, the navigation systems and transponder systems may comprise navigation systems and transponder systems of different types and may have different manufacturers. The communication systems, navigation systems, transponder systems, and other avionics systems may be communicatively connected to the aircraft avionics management and control system via different types of communication links having different communications protocols and/or different standards. | 10-09-2014 |
20140303814 | Aerial farm robot system for crop dusting, planting, fertilizing and other field jobs - Modern farming is currently being done by powerful ground equipment or aircraft that weigh several tons and treat uniformly tens of hectares per hour. Automated farming can use small, agile, lightweight, energy-efficient automated robotic equipment that flies to do the same job, even able to farm on a plant-by-plant basis, allowing for new ways of farming. Automated farming uses unmanned aerial vehicles (UAVs) that are equipped with detachable implements and reservoirs and that we call “aerial farm robots.” Automated farming uses high-precision GPS and other precision positioning and vision technology to autonomously and precisely perform crop dusting, planting, fertilizing and other field related farming or husbandry tasks. The subsystems for the control, refill, recharge and communication subsystems of the aerial farm robots are part of the overall automated farming system, and can autonomously handle most of the husbandry tasks on a farm. | 10-09-2014 |
20140303815 | METHOD FOR DETERMINING A TAXIING PATH OF AN AIRCRAFT OVER AN AIRPORT AREA - The general field of the invention is that of methods for determining a taxiing path of an aircraft over an airport area. The method is implemented by the avionics system of the aircraft. It comprises the following steps:
| 10-09-2014 |
20140303816 | AIRCRAFT INFORMATION MANAGEMENT SYSTEM - A method and apparatus comprising an existing aircraft node and an information agent located in the existing aircraft node. The existing aircraft node is connected to a number of aircraft systems and a network in an aircraft network data processing system. The information agent is configured to provide access to information received by the existing aircraft node to other aircraft nodes in the aircraft network data processing system. | 10-09-2014 |
20140309817 | METHODS AND SYSTEMS FOR DISPLAYING PROCEDURE INFORMATION ON AN AIRCRAFT DISPLAY - A method for displaying a flight path navigational procedure includes, but is not limited to, detecting with a position detecting system a current location of the aircraft, obtaining from an electronic storage device a plurality of flight path navigation procedures available for a geographic location, determining with a flight path analysis system a preferred flight path that will be taken by the aircraft, and displaying on a display unit a moving map corresponding with the current location of the aircraft and further displaying a depiction of the plurality of flight path navigation procedures on the moving map. The preferred flight path is displayed with a visual cue that visually differentiates the preferred flight path from the other flight paths of the plurality of flight path navigation procedures. | 10-16-2014 |
20140309818 | RAM AIR TURBINE AUTODEPLOYMENT LOGIC - A ram air turbine deployment module includes a normal power module that determines if normal power from an aircraft is available, an air-ground module that determines if the aircraft is off the ground, a ground-maintenance module that determines if the aircraft is presently having maintenance preformed, and decision logic that provides an output to a ram air turbine that deploys the ram air turbine if normal power from the aircraft is not available, the aircraft is off the ground, and the aircraft is not presently having maintenance performed. | 10-16-2014 |
20140309819 | METHODS FOR PREDICTING A SPEED BRAKE SYSTEM FAULT - Methods of predicting a speed brake fault in an aircraft having a speed brake system including multiple control surfaces, a handle for setting the position of the multiple control surfaces, and at least one control surface position sensor, the methods include receiving a position signal from the at least one position sensor, determining a variation in the position signal and predicting a fault in the speed brake system. | 10-16-2014 |
20140309820 | METHODS AND SYSTEMS FOR REQUESTING AND RETRIEVING AIRCRAFT DATA DURING FLIGHT OF AN AIRCRAFT - The disclosed embodiments relate to methods for requesting and retrieving aircraft data during flight of an aircraft. This aircraft data can be used to perform additional monitoring of aircraft sub-systems to detect an abnormal condition, and/or to identify one or more sources that are causing the abnormal condition. In one embodiment, aircraft data for one or more relevant parameters can be requested from the ground, measured on-board the aircraft, and stored in a data file that is then communicated back to personnel on the ground. The real-time aircraft data for one or more relevant parameters can then be analyzed to identify the one or more sources that are causing the abnormal condition. | 10-16-2014 |
20140316613 | Aircraft Performance Monitoring System - A method and apparatus for monitoring an aircraft. A current performance of the aircraft is identified during operation of the aircraft using a model of the aircraft and flight state data. A current capability of the aircraft is identified from the current performance of the aircraft. An operation is performed based on the current capability of the aircraft. | 10-23-2014 |
20140316614 | Drone for collecting images and system for categorizing image data - A data collection system provides a first computer media for collecting image data, a second computer media for analyzing the image data and locating anomalies in the image data, a third computer media for linking particular image data to address data of the property where the anomaly is present and a fourth computer media for generating a list of pertinent properties having similar anomalies by address. The image data collected by an unmanned aerial vehicle or drone. | 10-23-2014 |
20140316615 | METHOD AND APPARATUS FOR AIRCRAFT SENSOR AND ACTUATOR FAILURE PROTECTION USING RECONFIGURABLE FLIGHT CONTROL LAWS - A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix. The method and apparatus also provide a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. The method and apparatus also provide a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators. An exemplary aircraft for using the method and apparatus of a reconfigurable flight control system is a quad tilt rotor. The quad tilt rotor provides a variety of redundant and back-actuators, as such, having a robust and highly qualified reconfigurable flight control system is very desirable. | 10-23-2014 |
20140324253 | AUTONOMOUS CONTROL OF UNMANNED AERIAL VEHICLES - A control module for an unmanned aerial vehicle is provided. In one example, the control module includes a plurality of control modes, wherein each control mode represents a different autonomy setting, a command generator configured to generate a command causing a selection of a first of the plurality of control modes for the unmanned aerial vehicle, and an intelligence synthesizer that automatically switches the unmanned aerial vehicle between the selected first of the plurality of control modes and a second of the plurality of control mode upon detection of a trigger event. | 10-30-2014 |
20140330454 | Taxiing Aircraft Vicinity Visualization System and Method - According to an embodiment, a method provides information regarding the vicinity of a vehicle. The method includes, in the vehicle, providing a sensor signal representative of an environmental condition in a vicinity of the vehicle, transmitting the sensor signal over a power line in the vehicle, receiving the sensor signal transmitted over the power line and transmitting a corresponding wireless sensor signal in the vehicle, receiving the wireless sensor signal and recovering the sensor signal, and presenting the recovered sensor signal in a human-perceivable form. | 11-06-2014 |
20140330455 | ALTERNATIVE METHOD TO DETERMINE THE AIR MASS STATE OF AN AIRCRAFT AND TO VALIDATE AND AUGMENT THE PRIMARY METHOD - A method, apparatus, and computer program product for identifying air data for an aircraft. The lift for the aircraft is identified. The number of surface positions for the aircraft is identified. The angle of attack during flight of the aircraft is identified. A synthetic dynamic pressure is computed from the lift, the number of surface positions, and the angle of attack. | 11-06-2014 |
20140330456 | LANDING SITE DESIGNATION IN AN AUTONOMOUS DELIVERY NETWORK - A method and system of landing site designation in an autonomous delivery network are disclosed. In one embodiment, a landing server marks a geo-spatial location as an autonomous delivery location upon receiving a designation data communicated through a network by a recipient user. The designation data indicates the geo-spatial location as the autonomous delivery location based on at least one of a current geospatial location of a mobile device of the recipient user and a map view marking created by the recipient user through a computing device. The autonomous delivery location is associated with the recipient user and a navigation data is communicated through the network to an autonomous vehicle, directing the autonomous vehicle to the autonomous delivery location of the recipient user when a payload is requested by any one of the recipient user and a sending user to be physically delivered to the autonomous delivery location. | 11-06-2014 |
20140330457 | METHODS AND APPARATUSES FOR AUTONOMOUS FLIGHT TERMINATION - A flight safety assembly onboard an aerial vehicle includes a first sensor configured to sense first information related to flight of the aerial vehicle and a second sensor configured to sense second information related to the flight of the aerial vehicle. A sensor input is adapted to receive third information related to the flight of the aerial vehicle. A processor is operably coupled to the first sensor, the second sensor, and the sensor input. The processor is configured to determine three independent instantaneous impact points for the aerial vehicle by independently analyzing each of the first information, the second information and the third information. The processor is also configured to generate three independent onboard flight termination indicators for each of the three independent instantaneous impact points that intersects with a region to be protected. | 11-06-2014 |
20140336847 | METHOD FOR OPTIMIZING OPERATION OF AIRCRAFT GROUND TRAVEL DRIVE SYSTEM - A method is provided for automatically or manually. optimizing independent ground travel operation in an aircraft equipped with one or more self-propelled nose or main wheels powered by a driver means, wherein selected operating parameters indicative of optimized ground travel are monitored by sensors or detectors to provide data and information relating to the selected parameters during operation of the ground travel system. Selected operating parameters can include, for example, speed, direction of travel, torque, component thermal data aircraft location data, and operator inputs, commands, and feedback, as well as other operational data or information. Data is collected, recorded, and analyzed to enable changes to be made to the ground travel system components in real time automatically by intelligent software or manually by a system operator or at a later time to ensure optimum operation of the system. | 11-13-2014 |
20140336848 | SYSTEM AND METHOD FOR DETECTING, TRACKING AND ESTIMATING THE SPEED OF VEHICLES FROM A MOBILE PLATFORM - A method and system for measurement of ground based vehicle speed includes a movable platform that includes an unmanned aerial vehicle (UAV) located in proximity to a roadway, the UAV operates under control and navigation of a UAV control unit, and the UAV also carries camera and monitoring equipment, the camera and monitoring equipment including an onboard computing system, and a camera with a wide angle lens and a camera with a telephoto lens, the cameras being mounted on a pan/tilt device. An algorithm operated by the on-board computing system is used to detect and track vehicles moving on a roadway. The algorithm is configured to detect and track the vehicles despite motion created by movement of the UAV. The cameras mounted on the pan/tilt device are moved under the direction of the computer vision algorithm to maintain a target vehicle of the detected moving vehicles in view, and the speed of the target vehicle is measured. | 11-13-2014 |
20140343759 | METHODS AND SYSTEMS FOR AIRCRAFT GUIDANCE - Methods and systems for guiding an aircraft are disclosed herein. An example method includes determining, via a processor, a difference between an estimated time of arrival and a required time of arrival of an aircraft. The example method also includes determining if the difference exceeds a threshold time. The example method further includes determining a deviation between a predicted four-dimensional flight trajectory of the aircraft and a measured four-dimensional flight trajectory of the aircraft during flight if the difference does not exceed the threshold time. The example method also includes generating a speed command to reduce the deviation and updating a flight plan of the aircraft based on the speed command. | 11-20-2014 |
20140350753 | Method and system for aiding the navigation of an aircraft - A system including at least one global navigation database including data for aerial navigation and airport navigation of the aircraft and data mentioned on navigation maps, a central unit for carrying out a contextualized filtering of data intended for a display and received, at least in part, from said navigation database, and a display device for carrying out the display on one and the same screen, said display being based on information from said contextualized filtering. | 11-27-2014 |
20140358332 | METHODS AND SYSTEMS FOR CONTROLLING AN AIRCRAFT - Methods, aircraft, and instrumentation systems are provided. An aircraft instrumentation system includes a first sensor and a controller. The first sensor is configured to detect a first gesture within a first task envelope located in an aircraft. The controller is coupled with the first sensor and is configured to compare the first gesture with a plurality of stored gestures and generate an aircraft related task in response to a match between the first gesture and a stored gesture of the plurality of the stored gestures. | 12-04-2014 |
20140365035 | AIR VEHICLE CONTROL SYSTEM AND METHOD - A control actuation system (CAS) for positioning control effectors of an air vehicle, for steering the air vehicle, includes application of a control allocation matrix to measured positions of the control effectors or their actuators, as part of a feedback mechanism. The output from the control allocation matrix is used as an input for one or more controllers, the output of which is passed through an inverse control allocation matrix, to produce signals that are sent to control actuators to position the control effectors. The controller may use different gains for different of its inputs, for example applying a lower gain for a brake signal than for one or more of a pitch signal, a roll signal, and a yaw signal. The control actuation may make for a control system that is able to better withstand impaired performance or non-performance of some the control effectors. | 12-11-2014 |
20140365036 | ENGINE OPERATIONS SUPPORT SYSTEMS AND METHODS FOR REDUCING FUEL FLOW - An operations support system is provided for an engine receiving fuel. The system includes a diagnostic engine model unit configured to receive engine data from the engine and to generate diagnostics data based on the engine data, the diagnostics data including scalars. The system further includes an engine-specific model unit coupled to the diagnostic engine model unit and configured to receive the scalars and the engine data. The engine-specific model unit includes a fuel flow calculation module configured to determine a current fuel flow for the engine and a set point module configured to generate set point information for the engine using a thermodynamic model that reduces the current fuel flow to the engine, the thermodynamic model being based on component maps associated with the engine. The system further includes a data storage unit coupled to the engine-specific model unit and configured to store the set point information. | 12-11-2014 |
20140365037 | FAULT TOLERANT LATERAL WAYPOINT SEQUENCING SYSTEM AND METHOD - Fault-tolerant lateral waypoint sequencing is provided for a system that includes at least a first flight management computer and a second flight management computer. A processing operation associated with lateral leg sequencing of an aircraft flight plan is implemented in the flight management computers. A determination is made in the first flight management computer as to whether the first flight management computer has received, within a predetermined period of time from when the first flight management computer implemented the processing operation, a notification from the second flight management computer that the second flight has also implemented the processing operation. An action is initiated in the first flight management computer when the first flight management computer has not received the notification from the second flight management computer within the predetermined period of time. | 12-11-2014 |
20140365038 | Display System - A display system for displaying a layout of controls in a simulator including at least one of an information display, a switch such as a toggle or push-button switch, and a monitoring device such as an indicator, or a gauge, for a vehicle, the display system including a touch sensitive screen which is generally transparent over a significant portion of its area, and a plurality of projectors which project onto a back of the screen, images of the vehicle controls, the projectors each being operatively connected to a computer controller which responds to the front of the screen being touched where a depicted control is displayed, to change the display in a manner to mimic the result of a corresponding actual vehicle control being operated. | 12-11-2014 |
20140365039 | SYSTEM AND METHOD FOR MAXIMIZING AIRCRAFT SAFE LANDING CAPABILITY DURING ONE ENGINE INOPERATIVE OPERATION - A method of preserving rotor speed during a one engine inoperative operation of an rotorcraft, the method can include: detecting a failure of a first engine; monitoring an engine parameter associated with a second engine; using a computer processor to compare the engine parameter to an engine limit; and commanding a decrease collective pitch command when the engine parameter is within a predefined range of the engine limit. | 12-11-2014 |
20140365040 | METHODS AND SYSTEMS FOR BRIEFING AIRCRAFT PROCEDURES - Methods and systems are provided for providing procedure information associated with an aircraft procedure onboard an aircraft. An exemplary method involves obtaining a briefing sequence for the aircraft procedure and providing the procedure information via the output device, wherein the procedure information is provided in accordance with the briefing sequence. When the output device is realized as an audio output device, the procedure information is sequentially provided auditorily via the audio output device. In one or more embodiments, the procedure information is sequentially indicated on a display device onboard the aircraft in concert with the auditorily provided procedure information. | 12-11-2014 |
20140371956 | Systems and Methods for Moving a Load Using Unmanned Vehicles - An actual position of a load tethered with a tether to a vehicle is determined using a plurality of sensors disposed on the vehicle. A required tether tension and required tether angle of the tether is determined to move the load from the actual position to a commanded position. An actual tether tension and actual tether angle of the tether is determined using the plurality of sensors. A determination is made as to a thrust vector to be applied by the vehicle to change the actual tether tension and the actual tether angle of the tether to the required tether tension and the required tether angle. The thrust vector is applied with the vehicle to reposition the vehicle to achieve the required tether angle and to create the required tether tension of the tether to move the load to the commanded position. | 12-18-2014 |
20140371957 | METHOD AND DEVICE FOR DIAGNOSIS OF A LOSS OF CONTROL OF AN AIRCRAFT - A method for diagnosis of a loss of control of an aircraft comprises the steps: loading raw data; loading parameters of the aircraft; computing a plurality of reference data comprising a preprocessing comprising for at least one reference datum a sub-step of computing a phase advance term; determining the characteristic thresholds indicative of loss of control; detecting at least one type of loss of control by comparing the reference data with characteristic thresholds; and, when at least one type of loss of control is detected: identifying the type of priority loss of control corresponding to the type of loss of control exhibiting the highest priority level, and communicating the type of priority loss of control to a crew. | 12-18-2014 |
20140379176 | METHOD AND APPARATUS FOR SPACECRAFT ATTITUDE CONTROL USING POLYNOMIAL INTERPOLATION - A method, apparatus and system is provided for reducing an amount of information transmitted to a vehicle in order to implement attitude control of the vehicle. In accordance with the present invention, data corresponding to at least one time-varying attitude command trajectory defining an attitude of the vehicle is reduced, for example, into a vector of polynomial coefficients. The vector of polynomial coefficients then are transmitted to the vehicle, where they are used to reconstruct the at least one time-varying attitude command trajectory via a polynomial interpolation operation. | 12-25-2014 |
20150012153 | BRAKE CONTROL SYSTEM COMPRISING TIRE/RUNWAY FRICTION PROPERTY ESTIMATION MAPPING - Systems and methods for a tire/runway friction property estimation method based on measured wheel speed, calculated acceleration, wheel reference and tire normal force estimation are disclosed. Based on the resulting estimations, a map and/or function of position for the friction properties may be formed and transmitted to external systems after an aircraft stop is completed. | 01-08-2015 |
20150019047 | DISPLAY SYSTEMS AND METHODS FOR PROVIDING DISPLAYS HAVING AN INTEGRATED AUTOPILOT FUNCTIONALITY - A method for providing a display to a flight crew of an aircraft includes providing a horizontal navigation display that includes data regarding the movement of the aircraft in a horizontal direction and an aircraft icon indicating a position of the aircraft in the horizontal direction. The method further includes providing a vertical navigation display that includes data regarding the movement of the aircraft in a vertical direction and an aircraft icon indicating a position of the aircraft in the vertical direction. The horizontal and vertical navigation displays are disposed adjacent to one another on a single display device. The method further includes receiving a first input to the display device indicating a selection of the horizontal navigation display aircraft icon, and, in response to the selection of the horizontal navigation display aircraft icon, engaging a horizontal navigation control feature of an autopilot system of the aircraft. | 01-15-2015 |
20150025713 | AUTONOMOUS VEHICLE AND METHOD FOR COORDINATING THE PATHS OF MULTIPLE AUTONOMOUS VEHICLES - A non-transitory processor-readable medium storing code causes a processor at a first vehicle (e.g., a first autonomous vehicle) to generate a first planned path based on a current position of the first vehicle and a mission requirement assigned to the first vehicle. A first planned path associated with a second vehicle (e.g., a second autonomous vehicle), which is based on a current position of the second vehicle and a mission requirement assigned to the second vehicle, is received at the first vehicle. After the first planned path associated with the second vehicle is received, a second planned path is generated based on the first planned path associated with the second vehicle and at least one of the mission requirement assigned to the first vehicle or the first planned path of the first vehicle. The second planned path of the first vehicle is transmitted to the second vehicle. | 01-22-2015 |
20150032295 | VISUAL LOCALIZATION OF UNMANNED AERIAL VEHICLES BASED ON MARKER DETECTION AND PROCESSING - A method for locating markers in an image captured by a mobile device moving about an operating space. The method includes preprocessing an image to generate a set of image data, locating fixed features of markers by tracing edges of the fixed features, and extracting variable data payloads of each of the markers associated with the located fixed features. The fixed features of each of the markers may include a pair of parallel lines extending along opposite sides of a data area containing the variable data payload, and each of the lines extends a distance beyond each exposed end of the data area to avoid missing data when markers are not arranged orthogonally to the scan direction. The preprocessing involves rotating or skewing the image to provide rotated or skewed versions of the image to facilitate locating markers regardless of their angular orientation in the image. | 01-29-2015 |
20150032296 | AVIONICS SYSTEM ADAPTED FOR EMPLOYING SMARTPHONE TO INPUT-OUTPUT FLIGHT DATA - A system and method configured to monitor aircraft flight performance data. The system includes a wireless transmitter in data communication with an avionics system of the aircraft, a portable wireless transceiver associated with the wireless transmitter, and a wireless database associated with the wireless transmitter. The method includes sensing flight performance data with the sensor, transmitting sensed flight performance data to the wireless transmitter, wirelessly transmitting the sensed flight performance data to the wireless database, and monitoring flight performance data with a display operably associated with the wireless database. | 01-29-2015 |
20150032297 | ELECTRONIC FLIGHT TEST CARD - An electronic flight test card for testing a UAV (Unmanned Aerial Vehicle) design is provided. The flight test card comprises: a module comprising a list of tests to be performed, each test linked to a requirement for a system or subsystem of the UAV; an interface for communicating with the UAV; a storage medium with a data log for storing the test results captured by the interface; a display module for displaying test items; and an output for exporting the data log to a configuration system. | 01-29-2015 |
20150039159 | HARD LANDING DETECTION AND ORIENTATION CONTROL - Embodiments of the disclosure are directed to obtaining, by a device, data associated with an aircraft, processing, by the device, the data, determining, by the device, that the aircraft is likely to impact an object with a probability greater than a threshold within a second threshold amount of time based on the processed data, and causing, by the device, a change in an orientation of the aircraft based on the determination. | 02-05-2015 |
20150039160 | AIRCRAFT INCLUDING A SYSTEM FOR MEASURING PRESSURE, AND AN ASSOCIATED METHOD - The invention relates to an aircraft ( | 02-05-2015 |
20150039161 | Tethered Gyroglider Control Systems - A flight control system for at least one tethered gyroglider along a flight path consistent with at least one flight mission is configured to fly the gyroglider within a portfolio of winds, managing an interaction between portfolios of at least four envelopes including wind, gyroglider performance, flight and base station. Every flight mission corresponds to at least one flight path associated with a set containing at least one first value and at least one second value. The control system is provided with a learning and library manager comprising a repository having stored sets of first values and associated second values for each flight path. The current first values associated with a current mission are corrected based on predicted or experienced flight paths and measurable outputs to attain the desired flight path. The corrected, experienced values, flight path and measurable output are further stored in the repository for further learning. | 02-05-2015 |
20150045994 | SYSTEM AND METHOD FOR HIGHLIGHTING AN AREA ENCOMPASSING AN AIRCRAFT THAT IS FREE OF HAZARDS - A system and method display a hazard free area around an aircraft that is modified to alert a pilot if a threshold distance between a detected object and the aircraft is reached. The modification may include, for example, altering the size of the hazard free area and its color. Additional information that may be displayed includes distance to the object, width of the hazard free area, stopping distance of the aircraft, and a route to avoid the object. | 02-12-2015 |
20150045995 | Demand Based Field of View (FOV) Allocation for Remote Sensing Systems - The present disclosure provides a system, method, and apparatus for collecting sensor data by a remote vehicle. The method involves determining, by at least one first processor, at least one scene to collect by using information in a demand map. The method further involves configuring, by at least one processor, a field of view for at least one sensor associated with the remote vehicle to collect at least one scene. Further, the method involves collecting, by at least one sensor, at least one scene. | 02-12-2015 |
20150051756 | Aircraft System Control and Reporting via a Mobile Device - A method and apparatus for controlling a plurality of different systems on an aircraft. A mobile device is connected to an aircraft network on the aircraft. The mobile device is moveable to a plurality of different locations on the aircraft. The mobile device receives input from an operator identifying controls for controlling functions performed by the plurality of different systems on the aircraft. The controls are sent from the mobile device to the plurality of different systems on the aircraft via the aircraft network. | 02-19-2015 |
20150051757 | Method for Monitoring Autonomous Accelerated Aircraft Pushback - A method for monitoring an autonomous accelerated pushback process in an aircraft equipped with an engines-off taxi system is provided to maximize safety and facilitate the accelerated pushback process. The aircraft is equipped with a monitoring system including a number of different kinds of sensors and monitoring devices positioned to maximally monitor the aircraft's exterior ground environment and communicate the presence or absence of obstructions in the aircraft's path while the pilot is controlling the engines-off taxi system to drive the aircraft in reverse away from a terminal gate and then turn in place at a selected location before driving forward to a taxiway. The sensors and monitoring devices may be a combination of cameras, ultrasound, global positioning, radar, and LiDAR or LADAR devices, and proximity sensors located at varying heights adapted to continuously or intermittently scan or sweep the aircraft exterior and ground environment during aircraft ground movement. | 02-19-2015 |
20150057844 | METHOD FOR CONTROLLING A MULTI-ROTOR ROTARY-WING DRONE, WITH CROSS WIND AND ACCELEROMETER BIAS ESTIMATION AND COMPENSATION - The attitude and speed of the drone are controlled by angular commands applied to a control loop ( | 02-26-2015 |
20150066250 | FLIGHT MANAGEMENT SYSTEM TEMPLATES - A method is described for determining access to functionality of a flight management system. The method may include constructing at least one user profile and determining access to functionality of the flight management system using a role and a user profile. One or more roles and one or more user profiles may be identified for a user. Upon receiving a request from the user to perform an action, a determination may be made whether to perform the action by validating the role and user profile data contained in the user profile. After validating the role and the profile data, the action requested by the user may be performed. | 03-05-2015 |
20150066251 | FLUTTER CONTROL ACTUATOR - A method and apparatus for controlling an angular parameter between a base member and a control surface of an aircraft is disclosed. An estimate is obtained of an angular rate of the control surface with respect to an inertial frame of the aircraft using a rate sensor. A residual angular rate that is a difference between a commanded angular rate and the estimate of the angular rate of the control surface is determined. The residual angular rate is used to control the angular parameter of the control surface or the angular parameter of the base member. | 03-05-2015 |
20150066253 | SYSTEMS AND METHODS FOR FUEL MONITORING - A zero fuel time is determined and presented to an operator of an unmanned aerial vehicle (UAV). Zero fuel time may be determined based on a fuel burn rate and an amount of remaining fuel. A return to base time is determined and presented to an operator of a UAV. Return to base time may be determined based on a location of the UAV and a location of a base. Zero fuel time and return to base time are presented to an operator of a UAV proximate to one another using contrasting and/or varying visual characteristics to ease comparison and identification of this data. | 03-05-2015 |
20150073626 | AIRCRAFT WEIGHT IDENTIFICATION USING FILTERED TRIM ESTIMATION - Embodiments are directed to receiving, by a computing device comprising a processor, at least one control input associated with an aircraft, obtaining, by the computing device, a predicted response to the at least one control input by filtering on a trim position, wherein the predicted response is based on a model of the aircraft, obtaining, by the computing device, an actual response of the aircraft to the at least one control input, comparing, by the computing device, the predicted response and the actual response, and determining, by the computing device, at least one attribute based on the comparison | 03-12-2015 |
20150073627 | ROTOR TRACK AND BALANCE WITH IMPROVED LINEAR OPTIMIZATION - A method for reducing vibrations in an airframe of an aircraft includes determining, with a processor, information indicative of an initial error value between a desired vibration level and a measured vibration level in the airframe; determining, with the processor, an initial adjustment solution for the aircraft in response to the determining of the information for the initial error value; receiving, with the processor, information indicative of a flight response to the initial adjustment solution; combining, with the processor, disturbance signals indicative of vibration noise with the information for the flight response; determining, with the processor, a subsequent error value between the desired vibration level and a subsequent measured vibration level; and determining, with the processor, a predicted adjustment solution in response to the determining of the subsequent error value. | 03-12-2015 |
20150081137 | MESSAGING AND DATA ENTRY VALIDATION SYSTEM AND METHOD FOR AIRCRAFT - A system and method for validating data entry in response to an instruction received in an aircraft cockpit includes receiving, in an aircraft cockpit, an instruction that requires an aircraft pilot to manually enter a target value into an avionics system using an avionics system user interface. The received instruction is processed to determine the target value that should be set by the aircraft pilot using the avionics system user interface. Haptic feedback is to the avionics system user interface during the manual entry by the aircraft pilot. | 03-19-2015 |
20150081138 | AIRCRAFT SYSTEMS AND METHODS FOR DETECTING NON-COMPLIANT PILOT ACTION - Aircraft systems and methods for detecting non-compliant pilot action are provided. The method comprises analyzing an outbound communication from an aircraft to recognize a word or phrase corresponding to a parameter associated with a prior request for pilot action. If the word or phrase is recognized, the method further comprises storing data corresponding to the outbound communication in a data storage device. The stored data and pilot action taken are compared to determine if there is a discrepancy between the pilot action and the stored data. A discrepancy alert is outputted if the discrepancy is determined to exist. A predetermined time interval is timed from the outbound communication. A timeout alert is outputted at a timeout of the predetermined time interval unless the requested pilot action is taken within the predetermined time interval. | 03-19-2015 |
20150081139 | DEVICE AND METHOD FOR ACTIVE CONTROL OF A FORCE FEEDBACK FOR A CONTROL DEVICE - The invention concerns a device for the active control of a force feedback for a control device, comprising a calculator, a position sensor ( | 03-19-2015 |
20150081140 | ELECTRIC FLIGHT CONTROL SYSTEM AND METHOD FOR AN AIRCRAFT - A flight control system includes at least one flight domain protection module intended at least for manual piloting and an auxiliary element configured to automatically transmit to the protection module, upon a detection of automatic piloting of the aircraft using an automatic piloting device, a predetermined auxiliary position, representing a control stick position equivalent, the protection module using the auxiliary position as a control stick position to implement a flight domain protection during the automatic piloting. | 03-19-2015 |
20150081141 | METHOD AND SYSTEM FOR COORDINATING REMOVAL OF CONTAMINATION FROM SURFACE OF AIRCRAFT - A method for coordinating contamination removal on a surface of an aircraft, comprising receiving an electronic contamination removal request, determining location for contamination removal treatment, electronically transmitting location for contamination removal treatment to aircraft, electronically receiving progress of contamination removal treatment, and electronically transmitting progress of contamination removal treatment to aircraft, wherein the progress of contamination removal treatment is displayed on multiple displays to allow for close monitoring of the contamination removal treatment. | 03-19-2015 |
20150088340 | OPTIMIZED FLAP POSITIONING FOR GO-AROUND OPERATIONS - A system for optimizing a flap setting of an aircraft may include a flap optimizing computer configured to compute an optimum flap setting for one or more flaps of an aircraft. The system may further include a flap control system communicatively coupled to the flap optimizing computer. The flap control system may be operable to select any one of a plurality of flap settings including a designated flap setting. The flap control system may be configured to automatically command the one or more flaps from a first position to a second position corresponding to the optimum flap setting in response to the selection of one of the plurality of flap settings using the flap control system. | 03-26-2015 |
20150088341 | Control system for an aircraft - The control system of an aircraft including at least two communication networks and a controlled device control unit connected to one of them. The system determines control commands for the device with a DAL-A quality assurance level requirement and includes a set of at least three physical units each including at least two computers, an electrical power supply and a network interface device. The electrical power supplies, and the network interface devices, are of at least three different types, the computers are of at least two different types and include operating systems of at least two different types; the computers each have a DAL-C, DAL-D or DAL-E hardware and/or software quality assurance level and at least six of the computers are configured to independently determine control commands for the device. A DAL-A hardware and software quality assurance level selection logic unit is configured to select valid control commands used by the control unit to control the device. | 03-26-2015 |
20150094882 | PANEL AND SYSTEM FOR AIRCRAFT CABIN MANAGEMENT - An aircraft cabin management panel and an aircraft cabin management system including the aircraft cabin management panel. The aircraft cabin management panel includes a user interface and a control unit configured to communicate a control instruction to at least one of a plurality of cabin components provided in an aircraft cabin upon an input received via the user interface. The control instruction enables the at least one of the plurality of cabin components to perform an operation in accordance with the control instruction. | 04-02-2015 |
20150094883 | Multi-part Navigation Process by an Unmanned Aerial Vehicle for Navigation - Embodiments described herein may relate to an unmanned aerial vehicle (UAV) navigating to a target in order to provide medical support. An illustrative method involves a UAV (a) determining an approximate target location associated with a target, (b) using a first navigation process to navigate the UAV to the approximate target location, where the first navigation process generates flight-control signals based on the approximate target location, (c) making a determination that the UAV is located at the approximate target location, and (d) in response to the determination that the UAV is located at the approximate target location, using a second navigation process to navigate the UAV to the target, wherein the second navigation process generates flight-control signals based on real-time localization of the target. | 04-02-2015 |
20150100180 | ELECTRICITY GENERATION SYSTEM - An electricity generation system according to the present invention comprises a first electric generator designed to generate electricity by rotation of a high-pressure shaft of a compressor constituting a jet engine, a second electric generator designed to generate electricity by rotation of a low-pressure shaft of the compressor, a power distributor for distributing power generated by the first and second electric generators among a multiple loads, a first power regulation device for regulating power output of the first electric generator, a second power regulation device for regulating power output of the second electric generator, and a power control device which manipulates the first and second power regulation devices to ensure a specified amount or greater of jet engine surge margin. | 04-09-2015 |
20150100181 | Electrified Rotorcraft - An electrified propulsion system for a rotary wing aircraft includes a flight control computer that receives a signal indicative of a power demand on an engine; an engine control system that is in communication with the engine and is configured to control operation of the engine at a selected operating point; a generator that is in mechanical communication with the engine and is configured to receive mechanical power from the engine and convert the mechanical power to electrical power; an electric motor that is in electrical communication with the generator and is configured to receive the electric power; and a rotor that is in mechanical communication with the electric motor; wherein the electric motor is configured to control rotation and provide the mechanical power demand of the rotor at the selected operating point in response to the received signal. | 04-09-2015 |
20150100182 | METHOD FOR FIGHTER TAKEOFF AND LANDING WITHIN ULTRA-SHORT DISTANCE (ULTRA-STOL) - A method for a fix-wing fighter to take off and land on an ultra-short distance is disclosed. In one embodiment, a method for a fighter to take off with an ultra-short distance may include providing a runway on a predetermined height, wherein the runway is shorter than a normal runway; disposing the fighter at said runway; and providing the fighter with an initial speed and the fighter is able to accelerate on said runway; wherein the fighter reaches its takeoff speed (which is smaller than a normal takeoff speed of the fighter) at the end of the runway, and is then accelerated by a combination of the flighter's acceleration and gravitational acceleration until the fighter reaches its normal takeoff speed. | 04-09-2015 |
20150100183 | AIRCRAFT INSTRUMENT AND BACKUP POWER THEREFOR PROVIDED BY MAGNETO P-LEAD - An aircraft instrument includes an engine display area providing aircraft engine parameters simultaneously with an electrical system display area that selectively provides one of a plurality of aircraft electrical system parameter displays. In the event of an aircraft electrical power supply failure, the instrument may be automatically powered by otherwise unused energy safely harvested from one or all magneto P-leads of an aircraft via an energy harvesting circuit. | 04-09-2015 |
20150105945 | CONTROL INTERFACE FOR LEADING AND TRAILNG EDGE DEVICES - A system for controlling a high-lift device of an aircraft may include an interface for placement in a flight deck of an aircraft. The interface may include an edge control device for controlling a position of the high-lift device. The interface may be operable to select any of a plurality of control device positions. Each one of the plurality of control device positions may correspond to a different flight phase of the aircraft. The edge control device may be operable to engage, in response to a selection of a first control device position, a command mode for actuating the high-lift device in an automated manner based on the flight phase associated with the first control device position. | 04-16-2015 |
20150105946 | THREE-DIMENSIONAL MANIPULATION OF TEAMS OF QUADROTORS - A system and method is described for controlling flight trajectories of at least two flying vehicles towards goal positions. The system includes at least two flying vehicles with onboard inertial measurement units for determining and updating orientation, angular velocities, position and linear velocities of the at least two flying vehicles, a motion capture system to detect current position and velocity of each of the at least two flying vehicles, and a base controller in communication with the motion capture system and in communication with the plurality of flying vehicles. The base controller calculates for each of the flying vehicles, at predetermined intervals of time, optimum trajectory paths using piece-wise smooth polynomial functions, applying weighting factors, and enforcing overlap constraints. | 04-16-2015 |
20150112515 | Rotor Break Control System - According to one embodiment, a rotor brake control system includes a temperature sensor operable to measure an operating temperature of a rotor brake and a rotor brake control unit operable to instruct a caliper to adjust, based on the measured operating temperature, an amount of friction generated between a brake pad and the rotor brake. | 04-23-2015 |
20150112516 | AUTOMATIC FLIGHT CONTROL FOR UAV BASED SOLID MODELING - Technologies are generally described for controlling a flight path of a UAV based image capture system for solid modeling. Upon determining an initial movement path based on an estimate of a structure to be modeled, images of the structure to be modeled may be captured and surface hypotheses formed for unobserved surfaces based on the captured images. A normal vector and a viewing cone may be computed for each hypothesized surface. A set of desired locations may be determined based on the viewing cones for the entire structure to be modeled and a least impact path for the UAV determined based on the desired locations and desired flight parameters. | 04-23-2015 |
20150120090 | METHODS AND SYSTEMS FOR DISPLAYING AIRCRAFT INFORMATION - A method and an instrumentation system for an aircraft are provided. The method of presenting aircraft information includes activating a master indicator in response to a trigger event associated with operation of the aircraft, receiving a user input associated with the master indicator, and displaying information associated with the trigger event in response to receiving the user input associated with the master indicator. The instrumentation system performs the operations of the method. | 04-30-2015 |
20150120091 | COMPUTER IMPLEMENTED METHOD OF AIRCRAFT SELECTION - A computer implement method of aircraft selection involves providing parameters and a set of logic rules reflecting laws, regulations and policies relating to safe operation of an aircraft, along with a database of aircraft relating to a fleet of aircraft of the same type. There is input into a computer processor a request for an aircraft to fulfil a mission at a time a pilot declares readiness for an aircraft. The computer processor makes a selection from the database of aircraft a first subset of aircraft that are available and capable of safely performing the mission. | 04-30-2015 |
20150120092 | ICE AND SUPERCOOLED WATER DETECTION SYSTEM - A system for detecting ice or supercooled large droplets within an area of interest having a detection system measuring radiance or reflectance of the area of interest when exposed to shortwave infrared radiation having a wavelength in the range of about 2.05 μm to about 2.30 μm. The detection system measures the radiance or reflectance in a first band having a wavelength in the range of about 2.05 μm to about 2.15 μm and outputting a first band signal, and further measures the radiance or reflectance in a second band having a wavelength in the range of about 2.15 μm to about 2.30 μm and outputting a second band signal. A processing unit determines a ratio of the first band signal and the second band signal and compares the ratio to a predetermined critical ratio and outputs a determination signal indicating presence of ice or supercooled water droplets. | 04-30-2015 |
20150120093 | ICE AND WATER DETECTION SYSTEM - A system for detecting ice or water within an area of interest having a detection system measuring radiance or reflectance of the area of interest when exposed to shortwave infrared radiation having a wavelength in the range containing a crossover point between the curves representing the absorption of electromagnetic radiation by ice and water. The detection system measures the radiance or reflectance in a first band having a wavelength in a spectral band on a first side of the crossover point and outputting a first band signal, and further measures the radiance or reflectance in a second band having a wavelength in a spectral band on a second opposing side of the same crossover point and outputting a second band signal. A processing unit determines a ratio of the first band signal and the second band signal and compares the ratio to a predetermined critical ratio and outputs a determination signal indicating presence of ice or water. | 04-30-2015 |
20150120094 | UNMANNED AERIAL VEHICLE DELIVERY SYSTEM - This disclosure describes an unmanned aerial vehicle (“UAV”) configured to autonomously deliver items of inventory to various destinations. The UAV may receive inventory information and a destination location and autonomously retrieve the inventory from a location within a materials handling facility, compute a route from the materials handling facility to a destination and travel to the destination to deliver the inventory. | 04-30-2015 |
20150120095 | FLIGHT MANAGEMENT METHOD AND SYSTEM - A method is provided for managing the flight of an aircraft flying a trajectory calculated by a flight management system. The trajectory necessitates at least one transition between two different aerodynamic configurations of the aircraft. The method comprises: extraction of performance data of the aircraft from a database, at least one item of performance data being a function of an aerodynamic configuration, selection between a first determination step and a second determination step, a step of determination of a start point and of an end point of the transition between two aerodynamic configurations and engine speeds of an aircraft during a flight, the determination step being implemented by the flight management system and chosen from among the first and second determination steps, the determination step calculating the trajectory by numerical integration of the equations representative of the dynamics of the aircraft making use of the performance data of the aircraft. | 04-30-2015 |
20150127195 | SYSTEM AND METHOD FOR INDEPENDENT BRAKING SYSTEM ENABLEMENT - Described herein is a system and method to enable braking system operation independent of conventional aircraft signals, such as those tied to the hibernation commands. Stated another way, the present disclosure relates to the enablement of a braking system in response to an initiation signal. In this way, the crew has the ability to force the braking system out of a hibernation mode into an “emergency type” braking mode if desired. The concepts described herein may be applicable to an electric braking system and to a hydraulic braking system. | 05-07-2015 |
20150134149 | PILOT INTERFACE FOR AIRCRAFT ELECTRIC TAXI SYSTEM - A pilot interface panel may comprise at least one input mechanism configured to receive at least one user input, generate at least one input signal corresponding to the at least one user input, and send the at least one input signal to a controller. The controller may be configured to control movement of an electric taxi system of an aircraft in a manner according to the at least one input signal, wherein the electric taxi system may be configured to rotate at least one wheel of the aircraft by force from a purely electromotive source. The pilot interface panel may further comprise at least one safety mechanism, which may be configured to prevent at least one of the at least one input mechanisms from receiving an inadvertent user input resulting from an unintended action by the user. | 05-14-2015 |
20150134150 | AIRCRAFT AVOIDANCE METHOD AND DRONE PROVIDED WITH A SYSTEM FOR IMPLEMENTING SAID METHOD - A method enabling an aerial drone not having a TCAS system to avoid an intruder aircraft, the method including the steps of acquiring the position of the intruder aircraft in order to determine the distance between the aerial drone and the intruder aircraft, measuring the angular speed of the intruder aircraft in a horizontal plane, and determining whether the intruder aircraft is fitted with a TCAS system, and, if so, receiving a resolution advisory transmitted by the TCAS of the intruder aircraft and following a previously-determined avoidance path. The invention also provides a drone fitted with a system implementing the method. | 05-14-2015 |
20150134151 | ENGINE FUEL DELIVERY SYSTEM - This invention concerns a fuel delivery system for an aircraft engine, including a fuel delivery regulator arranged to receive fuel from a plurality of fuel sources for supply to the engine. An engine operating condition sensor reading is received by a control unit arranged to control operation of the regulator. The control unit actuates the regulator based on a received signal from the engine operating condition sensor in order to vary the volume of fuels from the plurality of fuel sources supplied to the engine during at least a portion of the landing/take-off (LTO) cycle relative to a further portion of the aircraft flight. The different fuels may include kerosene and an alternative fuel, such as a biofuel. | 05-14-2015 |
20150134152 | INTEGRATED REMOTE AERIAL SENSING SYSTEM - A system for high temporal and high spatial resolution monitoring of a field of plants is disclosed. Illustratively, the system includes a plurality of ground based reference objects, a balloon adapted to be positioned above the field of plants, and a balloon positioning system coupled to the balloon and configured to position the balloon relative to the field of plants. An imaging system is supported by the balloon and includes a locations system, at least one camera, and at least one gimbal configured to orient the at least one camera. The imaging system captures at least one image of the field of plants including the plurality of ground based reference objects in the at least one image. | 05-14-2015 |
20150134153 | SUPERVISION DEVICE FOR AN AIRCRAFT, ASSOCIATED SUPERVISION SYSTEM, SUPERVISION METHOD, COMPUTER PROGRAM PRODUCT AND NON-TRANSITORY COMPUTER READABLE MEDIUM - A supervision device for an aircraft including a plurality of avionics systems, each avionics system being able to generate parameters representative of its operation on a reference date, includes a plurality of prediction modules, each prediction module including a computer for computing projections representative of the trajectory of the aircraft and/or representative of the operation of at least one avionics system on a corresponding prediction date, the prediction date being after the reference date, at least one projection computed by a prediction module depending on at least one other projection computed by another prediction module. | 05-14-2015 |
20150142214 | MONITORING AND CONTROL SYSTEM FOR ENHANCING GROUND MOVEMENT SAFETY IN AIRCRAFT EQUIPPED WITH NON-ENGINE DRIVE MEANS - An improved monitoring and control system capable of providing automatic control of ground movement in an aircraft equipped with non-engine drive means for autonomous ground movement to enhance airport ground safety and efficient ground travel is provided. The monitoring and control system is installed on aircraft equipped with non-engine drive means controllable to move the aircraft autonomously on the ground and includes monitoring means positioned in locations on the aircraft selected to obtain a maximum amount of information relating to an aircraft's ground position and operation, processor means, data transmission means, and manual or automatic control means to control and direct operation of an aircraft's non-engine drive means to move the aircraft autonomously, safely and efficiently on the ground. The improved monitoring and control system can be employed with one or a number of aircraft simultaneously to increase safety and efficiency of airport ground operations. | 05-21-2015 |
20150142215 | Fly-By-Wire Engine Power Control System - According to one embodiment, a method of managing pilot and copilot control of engine power in an aircraft includes receiving, from a first pilot input device, a first signal representative of a pilot selection of an increase power position or a decrease power position and receiving, from a second pilot input device, a second signal representative of a pilot selection of an increase power position or a decrease power position. One of the first signal and the second signal is prioritized. An aircraft engine is then instructed to change power output based on the prioritized signal. | 05-21-2015 |
20150142216 | GAS TURBINE ENGINE TURBINE BLADE TIP ACTIVE CLEARANCE CONTROL SYSTEM AND METHOD - A system and method of controlling turbine blade tip-to-static structure clearance in a gas turbine engine includes processing aircraft data to determine when the aircraft is flying at altitude cruise conditions. When the aircraft is not flying at altitude cruise conditions, then compressor discharge air is directed to impinge upon at least a portion of the turbine shroud. Upon determining that the aircraft is flying at altitude cruise conditions, the compressor discharge air is directed to flow across at least a portion of the turbine case and to impinge upon at least a portion of the turbine shroud. | 05-21-2015 |
20150142217 | BRAKE CONTROL INITIATION USING TIRE RUNWAY FRICTION MAP DATA - In various embodiments, a method for utilizing a determined coefficient of friction along a portion of a runway is disclosed. The method may include receiving, by a brake control unit, friction estimation map data for a specific runway. The method may include setting, by the brake control unit, a condition of the braking control algorithm based on the received friction estimation map data. The method may include initiating, by the brake control unit, a brake control system to slow a wheel of an aircraft based on the braking control algorithm. | 05-21-2015 |
20150142218 | GUIDING METHOD FOR AIRCRAFT DOCKING PROCESS - A guiding method for aircraft docking process, which is used to detect an aircraft when docking to a stop line along a J-line on apron, includes steps as followed. According to response distances of different positions from a laser scanner, a distance between the aircraft and the stop line and offset angle during the docking process are detected. To show the distance and offset angle on a data display panel as guiding reference when a pilot of the aircraft operates the aircraft. The guiding method further has a waiting stage, a positioning stage, and a distinguishing stage and a guiding stage. | 05-21-2015 |
20150142219 | LOW SPEED AUTOGYRO YAW CONTROL APPARATUS AND METHOD - Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion device, such as an air jet or a fan may be used. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. Apparatus for generating horizontal lift imbalance induced a tail boom positioned within the downwash of a rotor may also be used, including compressed air vents or lateral or trailing edge flaps. | 05-21-2015 |
20150142220 | Method and device for automatically guiding an aircraft taxiing on the ground - A device comprises a monitoring unit configured to automatically monitor the actuation of a manual control member suitable for controlling an aircraft on the ground, so as to be able to detect a releasing of the control member in a neutral position. A computation unit is configured to compute a virtual axis for guiding the aircraft on the ground, upon the detection of the releasing of the control member in the neutral position. A guiding unit is configured to automatically guide the aircraft along said virtual axis. | 05-21-2015 |
20150142221 | METHOD FOR DETERMINING A RESULT PATH OF AN AIRCRAFT, ASSOCIATED DEVICE AND COMPUTER PROGRAM PRODUCT - A method for determining a result path of an aircraft, the result path including a set of successive positions of the aircraft between an initial global point and a final global point that are predetermined for a mission of the aircraft is provided. | 05-21-2015 |
20150142222 | APPARATUS AND METHOD FOR TRACING FLIGHT PLAN STATUS - An apparatus and a method for tracing a flight plan status are disclosed. The apparatus for tracing a flight plan status includes: a flight plan structure generation unit configured to generate a flight plan status transition structure based on received flight plan information; a flight plan setting unit configured to set a flight plan status based on a flight message transferred through an aeronautical fixed telecommunication network; and a flight plan tracing unit configured to trace the flight plan status included in the flight plan status transition structure based on the set flight plan status. | 05-21-2015 |
20150148991 | Method and Apparatus for Optimizing a Load in a Flight Control System While an Aircraft is on the Ground - A method, apparatus, and computer program product for managing movement of a flight control surface on an aircraft. A control signal is received to move the flight control surface to a position. Travel in a number of actuators in a plurality of actuators coupled to the flight control surface is limited to an amount that reduces a load on the number of actuators in the plurality of actuators in response to receiving the control signal while the aircraft is on the ground and the speed of the aircraft is less than a threshold. | 05-28-2015 |
20150148992 | Determining a Profile for an Aircraft Prior to Flight Using a Fuel Vector and Uncertainty Bands - A weight and center-of-gravity profile for an aircraft is determined prior to flight. An uncertainty band is determined for each of a plurality of points along a fuel vector for the planned flight. Each of the points along the fuel vector is compared to a predetermined flight limit (e.g., an FAA certified envelope). This comparison is used to decide whether the profile is suitable for flight of the aircraft. If so, an indication is provided to a user (e.g., on a display or by a text message) that the profile is suitable and the aircraft is ready for flight. | 05-28-2015 |
20150148993 | METHOD FOR PROVIDING PREDEFINED DRIVE CHARACTERISTICS IN AN AIRCRAFT, AND ASSOCIATED DRIVE DEVICE - The invention relates to a method for providing predefined desired drive characteristics ( | 05-28-2015 |
20150148994 | ENGINE CONTROL COMPUTER OF AIRCRAFT, AND AIRCRAFT - The invention deals with the restriction on the mode change of an engine due to latching in the case of restarting the engine that has stopped in flight. A FADEC that controls an engine of an aircraft in accordance with a mode, includes a latch operating section that latches the mode, and an in-parking/in-flight determining section that determines whether the aircraft is on the ground or flying off the ground. The latch operating section operates when the in-parking/in-flight determining section determines the aircraft is on the ground, and does not operate when the in-parking/in-flight determining section determines that the aircraft is in fight. | 05-28-2015 |
20150148995 | Aircraft Power Management System And Method For Managing Power Supply In An Aircraft - An aircraft power management system includes an electrical power supply input configured to be coupled to an electrical power supply, a first power supply bus bar coupled to the power supply input, at least one primary electrical equipment including a primary load coupled in parallel to the first power supply bus bar, a bus bar switch configured to selectively deactivate the first power supply bus bar downstream of the at least one primary electrical equipment, a load monitoring device configured to monitor the power demand of the primary load and to output a deactivation signal to the bus bar switch for selectively deactivating the first power supply bus bar, if the monitored power demand of the primary load exceeds a primary threshold, and at least one tertiary electrical equipment including a tertiary load coupled to the first power supply bus bar downstream of the at least one primary electrical equipment. | 05-28-2015 |
20150148996 | FLIGHT MANAGEMENT SYSTEM OF AN AIRCRAFT - A flight management system architecture with two separate modules is proposed. In the core module, generic functionalties relative to the flight management of the aircraft are implemented. In the supplementary module, supplementary functions are implemented. The supplementary functionalities include functionalties specific to an entity to which the aircraft belongs such as the specific aircraft model, a family of airdraft, a company, an alliance, and so on. The flight management system also includes a message exchange interface in which enables the core and supplementary modules to exchanges messages with each other. The core and supplementary modules includes corresponding core module and supplementary module interfacing functionaltities that respectively interface with generic and specific man-machine interfaces. | 05-28-2015 |
20150148997 | METHOD FOR FUSING DATA FROM SENSORS USING A CONSISTENCY CRITERION - The disclosure relates to a data fusion method for fusing the measurements of a parameter, for example an aircraft flight parameter, that are taken by a plurality of sensors comprising a set of main sensors and sets of secondary sensors. The discrepancy between each main measurement and the secondary measurements is determined and a score of consistency with them is deduced therefrom. For each fault configuration of the main sensors, a first estimation, so-called conditional, of the parameter is performed and a weighting coefficient relating to this fault is calculated, taking account of the consistency scores of the main measurements. The parameter is thereafter estimated by performing a combination of the conditional measurements with the associated weighting coefficients. | 05-28-2015 |
20150148998 | FLIGHT MANAGEMENT SYSTEM OF AN AIRCRAFT - A flight management system with core and supplementary modules is proposed. The core module may include generic applications that implement generic functionalities related to a flight management of the aircraft. The supplementary module may include supplementary applications that implement supplementary functionalities specific to an entity to which the aircraft belongs. The supplementary module may be divided into principal and auxiliary partitions (or entities), and the supplementary applications, also referred to as principal applications, may be implemented in the principal partition. One or more auxiliary applications may be implemented in the auxiliary partition. Each auxiliary application may be associated with one or more principal applications such that the execution of the principal application requires the associated auxiliary application to be executed. | 05-28-2015 |
20150148999 | MISSION MANAGEMENT SYSTEM OF AN AIRCRAFT - A mission management system to manage both ground and flight phases of a mission of an aircraft is proposed. The mission management system may be implemented in flight management system architecture with core and supplementary modules distinct from each other. The core module may implement a set of generic functionalities related to a flight management of the aircraft, and the supplementary module may implement supplementary functionalities specific to an entity to which the aircraft belongs. The mission management system may include a flight management unit to define and manage a flight plan and associated flight trajectory, an airport navigation unit to define and manage a ground plan and associated ground trajectory, and a mission management unit to manage a continuity between the ground and flight phases of the mission and prediction computations made by the flight management and the airport navigation units. | 05-28-2015 |
20150291277 | DECELERATION TO HOVER MODULATION - A system and method for controlling a deceleration profile of an aircraft, includes a processor and memory that receives a signal indicative of a deceleration command; receives signals indicative of a sensed velocity and a commanded heading rate; determines a commanded velocity in response to the receiving of the deceleration command and the commanded heading rate; determines an estimated deceleration command as a function of the commanded velocity; and determines an actual deceleration command in response to the determining of the estimated deceleration command. | 10-15-2015 |
20150292348 | DEVICE AND METHOD FOR PROTECTING AN AIRCRAFT TURBOMACHINE COMPUTER AGAINST SPEED MEASUREMENT ERRORS - A device protecting an aircraft turbomachine computer against speed measurement errors, including: on a speed regulation channel: a speed sensor of a turbomachine gearbox shaft, a speed measurement circuit, and a speed regulation circuit; on a monitoring channel: a speed sensor of a turbomachine gas generator shaft, a speed measurement circuit, and a turbomachine stop control circuit. Each channel uses dissimilar characteristics eliminating common mode errors. Each speed sensor delivers a pseudo-sine frequency signal. On each channel, speed monitoring circuits compare the frequency signal with a minimum threshold, delivering an error signal when the measured frequency is lower than the minimum threshold. A common speed cross checking circuit detects exceeding a determined deviation between both frequencies, the monitored deviation being higher or lower than a maximum deviation corresponding to loss of a frequency period on either sensor. Analyzing the error signals, exceeding the determined deviation can control stopping the turbomachine. | 10-15-2015 |
20150298788 | TRANSFORMABLE AERIAL VEHICLE - Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle. | 10-22-2015 |
20150298816 | CHECKLIST DISPLAY SYSTEM, METHOD AND GRAPHICAL DISPLAY THEREFOR - The present disclosure relates to a check-list display system ( | 10-22-2015 |
20150298817 | E-TAXI PREDICTIVE PERFORMANCE SYSTEM - An electric taxi predictive performance system may provide a predicted performance for an electric based taxi system (eTaxi) based on environmental information related to a vehicle. In some embodiments, the vehicle may be an aircraft using eTaxi systems to move around an airport runway system. The electric predictive taxi performance system may provide real-time displayed data to help pilots evaluate eTaxi capabilities of the aircraft as conditions change. | 10-22-2015 |
20150301530 | DAMAGE ADAPTIVE CONTROL - Embodiments of the disclosure are directed to measuring, via at least one sensor, at least one of a damage and a compromise associated with a vehicle, determining at least one of a region and a location of the at least one of a damage and a compromise and a level of the at least one of a damage and a compromise, and adapting an operational envelope for the vehicle based on the determined at least one of a region and a location of the at least one of a damage and a compromise and the level of the at least one of a damage and a compromise. | 10-22-2015 |
20150301531 | LANDING GEAR FORCE AND MOMENT DISTRIBUTOR - A landing gear force and moment distributor system for an aircraft having a longitudinal axis aligned in a forward-aft direction, a vertical axis perpendicular to the longitudinal axis, and a landing gear including a pair of bogies arranged symmetrically about the longitudinal axis, each bogie having an actuator arranged to brake and/or drive one or more wheels. The force distribution system includes a distribution module arranged to: receive an input demand including a longitudinal force input demand corresponding to a desired braking or driving force along the longitudinal axis for the landing gear and a moment input demand corresponding to a desired moment about the vertical axis for the landing gear; and to use the received input demand to calculate an output command including, for each bogie, a longitudinal force output command corresponding to a braking or driving force along the longitudinal axis to be applied to the bogie | 10-22-2015 |
20150307186 | ACTIVE VIBRATION CONTROL SYSTEMS AND METHODS FOR VEHICLES - Active vibration control systems ( | 10-29-2015 |
20150310746 | METHOD AND ASSEMBLY FOR GUIDANCE OF AN AIRCRAFT DURING A LOW-ALTITUDE FLIGHT - A method and assembly for guidance of an aircraft during a low-altitude flight. The guidance assembly comprises a memory forming part of a flight management system, which is configured to store an active flight trajectory and any new flight trajectory, generated by the flight management system, and a memory forming part of a guidance system, which is configured to also store the flight trajectory and any new flight trajectory, which are received from the flight management system, the guidance assembly being configured to periodically transmit from the guidance system to the flight management system identification codes for the flight trajectories recorded in the memory of the guidance system. | 10-29-2015 |
20150314853 | CONTROL DEVICE FOR AN ENGINE - An engine control device having a calculator for calculating a pitch setpoint for at least one propeller of the engine, the calculator taking account at least of a flight speed. | 11-05-2015 |
20150314854 | METHOD AND DEVICE FOR AUTOMATICALLY COMPARING FLIGHT TRAJECTORIES OF AIRCRAFT - A method and device for automatically comparing two flight trajectories for an aircraft includes a central processing unit having a first comparison element for automatically comparing lateral trajectories of the two flight trajectories, and a second comparison element for automatically comparing vertical trajectories of these two flight trajectories, these comparisons being carried out successively leg by leg of the flights, these comparisons being carried out as long as the respective successive legs are identical and at least for a predefined distance in the horizontal plane. | 11-05-2015 |
20150314855 | COAXIAL ROTOR LOW-SPEED MIXING - A system and method for estimating rotor mixing commands for an aircraft includes receiving signals indicative of reference commands from one or more controllers; receiving signals indicative of airspeed and sideslip angle for the aircraft, the sideslip angle being indicative of a direction of flight for the aircraft; calculating a sine and cosine of the sideslip angle; determining gains for roll and pitch as a function of the airspeed, the determining including referencing a look-up table that indexes the gain constants with the airspeed; and determining the one or more rotor mixing commands from the determined gains, the one or more rotor mixing commands being applied synchronously to the rotors in the aircraft. | 11-05-2015 |
20150314869 | POWER MANAGEMENT METHOD AND SYSTEM FOR AN UNMANNED AIR VEHICLE - Power management method and system for an unmanned air vehicle, wherein the unmanned air vehicle comprises a plurality of power demanding subsystems and a plurality of power sources. The invention establishes mission oriented fixed parameters. A fuzzy logic power management unit, comprised in the system, automatically calculates and assigns priorities for delivering power to the subsystems. It also automatically calculates and assigns amounts of power delivered to each subsystem and automatically decides which of the power sources to deliver power to which subsystem. The fuzzy logic power management system calculates and assigns the priorities and loads in function of a plurality of internal variables, external variables and the mission oriented fixed parameters. | 11-05-2015 |
20150314870 | MICRO UNMANNED AERIAL VEHICLE AND METHOD OF CONTROL THEREFOR - A micro unmanned aerial vehicle or drone (“UAV”) | 11-05-2015 |
20150316438 | METHOD FOR DETERMINING AIRCRAFT CENTER OF GRAVITY INDEPENDENT OF MEASURING THE AIRCRAFT WEIGHT - A method which determines aircraft Center of Gravity independent of measuring the aircraft weight. The method is used in monitoring, measuring and computing the Center of Gravity of an aircraft utilizing pressurized, telescopic landing gear struts with axles. Pressure sensors are mounted in relation to each of the landing gear struts to monitor, measure and record aircraft landing gear strut loads by way of pressure. Axle deflection sensors are mounted in relation to each of the landing gear axles to monitor, measure and record aircraft landing gear axle loads by way of deflection. Nose landing gear strut pressure and corresponding values from axle deflection sensors may be adjusted in correlation to the reduced size of the nose landing gear, as compared to the size of the main landing gear, allowing aircraft Center of Gravity to be determined from the combined measured main landing gear pressures in relation to a nose landing gear strut pressure measurements, or combined main landing gear axle deflection sensor in relation to a nose landing gear axle deflection sensor; without any determination of the aircraft weight. | 11-05-2015 |
20150316926 | WIRELESS ENGINE MONITORING SYSTEM AND ASSOCIATED ENGINE WIRELESS SENSOR NETWORK - A plurality of wireless engine sensors each includes a sensing circuit that senses an engine parameter as engine data. A radio transceiver receives and transmits the engine data regarding the sensed engine parameters. An engine monitoring module includes a housing configured to be mounted at the aircraft engine. A sensor receiver is mounted within the housing and receives the engine data from the wireless engine sensors. A first wireless transmitter is carried by the housing. A memory is carried by the housing and a processor is carried by the housing and coupled to the memory and the first wireless transmitter and configured to collect and store in the memory engine data related to engine parameters sensed during operation of the aircraft engine by the plurality of wireless engine sensors and transmit the engine data via the first wireless transmitter. | 11-05-2015 |
20150323641 | LOCATION DETECTION SYSTEM METHOD AND APPARATUS - The present application relates to an emergency location system for transportation vessels. The vessels are either aircraft or watercraft. The system includes an elevation device and a tether used to couple the elevation device to the aircraft or watercraft. The length of the tether is adjustable before and after an emergency has occurred. The elevation device is used to elevate beacons and visual indicators relative to the vessel to increase the detectability. An automated control system regulates deployment and operation of the tether and elevation device. | 11-12-2015 |
20150323932 | AUTONOMOUS CARGO DELIVERY SYSTEM - The present invention is directed to a system and methods of providing platform-agnostic systems and methods capable of providing an integrated processor and sensor suite with supervisory control software and interfaces to perform small unit rapid response resupply and CASEVAC into hazardous and unpredictable environments. | 11-12-2015 |
20150332490 | METHOD FOR ASSISTING THE NAVIGATION OF AN AIRCRAFT WITH CORRELATION OF DYNAMIC INFORMATION WITH A 4D FLIGHT TRAJECTORY - A method for assisting the navigation of an aircraft comprises: assembly by families of data by a processing unit of predetermined data and acquired data, including meteorological data, the families being predefined, each data value being associated with a time window of validity; formatting the data of the families to associate with each data value a type of graphical representation as text or a scalar, vector, surface, or volume; selection of families of data to be displayed; choice of a display time window for each family of data to be displayed; spatio-temporal discretization of the trajectory; spatio-temporal correlation of the discretized trajectory with each family of data as a function of the time windows of validity, in the display time windows of the family, to extract a sub-assembly from each family of data, by the processing unit; display of the sub-assemblies in a single representation on the same display screen. | 11-19-2015 |
20150336669 | UNMANNED AERIAL VEHICLE NETWORK-BASED RECHARGING - A device receives a request for a flight path for a UAV to travel from a first location to a second location, and determines capability information for the UAV based on component information of the UAV. The device calculates the flight path based on the capability information, identifies multiple recharging stations located on or near the flight path, and selects a recharging station from the multiple recharging stations based on one or more factors. The device generates flight path instructions, for the flight path, that instruct the UAV to stop and recharge at the recharging station. The device provides the flight path instructions to the UAV to permit the UAV to travel from the first location to a location of the recharging station, stop and recharge at the recharging station, and travel from the location of the recharging station to the second location via the flight path. | 11-26-2015 |
20150336671 | METHOD FOR ADAPTIVE MISSION EXECUTION ON AN UNMANNED AERIAL VEHICLE - A method for adaptive mission execution by an unmanned aerial vehicle includes receiving a set of pre-calculated mission parameters corresponding to an initial UAV mission; collecting UAV operation data during flight of the unmanned aerial vehicle; calculating a set of modified mission parameters from the set of pre-calculated mission parameters and the UAV operation data, the set of modified mission parameters corresponding to a modified UAV mission; and executing the modified UAV mission on the unmanned aerial vehicle. | 11-26-2015 |
20150336676 | AIRFOIL ICING CONTROLLER APPARATUSES, METHODS AND SYSTEMS - The AIRFOIL ICING CONTROLLER APPARATUSES, METHODS AND SYSTEMS (“AIC”) transforms weather and flight parameter data via AIC components into icing determinations and icing avoidance optimized flight plans based on airfoil type. In one implementation, the AIC comprises a processor and a memory disposed in communication with the processor and storing processor-issuable instructions to receive anticipated flight plan parameter data, obtain weather data based on the flight plan parameter data, obtain atmospheric data based on the flight plan parameter data, and determine a plurality of four-dimensional grid points based on the flight plan parameter data. The AIC may then determine a percent power increase (PPI) required by the aircraft to overcome power loss due to icing conditions. With dynamic, (near) real-time icing information and/or predictive icing forecast specific to airfoil type, the AIC may allow aircraft to efficiently avoid areas where PPI is greater than a predetermined percentage and/or avoid areas where dangerous icing may occur. | 11-26-2015 |
20150338854 | HIGH AUTHORITY STABILITY AND CONTROL AUGMENTATION SYSTEM - A method of increasing the control authority of redundant stability and control augmentation system (SCAS) actuators by utilizing feedback between systems such that one system may compensate for the position of a failed actuator of the other system. Each system uses an appropriate combination of reliable and unreliable inputs such that unreliable inputs cannot inappropriately utilize the increased authority. Each system may reconfigure itself when the other system actuator fails at certain positions so that the pilot or other upstream input maintains sufficient control authority of the aircraft. | 11-26-2015 |
20150338855 | CONTROLLING UNMANNED AERIAL VEHICLES AS A FLOCK TO SYNCHRONIZE FLIGHT IN AERIAL DISPLAYS - A system for flock-based control of a plurality of unmanned aerial vehicles (UAVs). The system includes UAVs each including a processor executing a local control module and memory accessible by the processor for use by the local control module. The system includes a ground station system with a processor executing a fleet manager module and with memory storing a different flight plan for each of the UAVs. The flight plans are stored on the UAVs, and, during flight operations, each of the local control modules independently controls the corresponding UAV to execute its flight plan without ongoing control from the fleet manager module. The fleet manager module is operable to initiate flight operations by concurrently triggering initiation of the flight plans by the multiple UAVs. Further, the local control modules monitor front and back end communication channels and, when a channel is lost, operate the UAV in a safe mode. | 11-26-2015 |
20150344017 | AIRCRAFT BRAKE SYSTEM TESTING METHODS - Methods for testing the operation of an aircraft braking system utilize the steps of applying a predetermined electrical energy level to an electromechanical actuator attached to a brake assembly, followed by discontinuing electrical energy to the electromechanical actuator. In some test methods, an actuation level of the electromechanical actuator is determined and used to evaluate braking performance. In other tests, a voltage generated by an electric motor in an actuator is measured and used to evaluate braking performance. | 12-03-2015 |
20150344126 | METHOD FOR IMPROVING CROSSWIND STABILITY OF A PROPELLER DUCT AND A CORRESPONDING APPARATUS, SYSTEM AND COMPUTER READABLE MEDIUM - Various embodiments provide a method for improving crosswind stability of a propeller duct. The method comprises defining an initial duct section based on a predetermined airfoil section having an initial value of a geometric parameter such that the geometric parameter of a portion of the initial duct section has the initial value. The method also comprises determining fluid flow paths around the initial duct section when subject to a crosswind having a predetermined crosswind speed. The method further comprises varying the initial value of the geometric parameter of the initial duct section to a threshold value which causes separation of fluid flow paths at a windward side of the initial duct section at and above the predetermined crosswind speed to form an improved duct section. Various embodiments provide a corresponding apparatus, system and/or computer readable medium. | 12-03-2015 |
20150344129 | AUTOBRAKING SYSTEM WITH COURSE TRAJECTORY ADJUSTMENT - Methods and systems are provided for improved autobraking systems for aircraft. Such systems and methods include a pedal balance controller configured to receive one of a yaw angle, a yaw speed, and a wheel speed, and an autobrake pedal executive module configured to send an autobrake left pedal command and an autobrake right pedal command to a pedal executive module, wherein the pedal executive module is configured to execute a pedal command. These systems and methods may assist a pilot in maintaining a desired course during autobraking. | 12-03-2015 |
20150344136 | MOBILE COMPUTING DEVICE-BASED GUIDANCE NAVIGATION AND CONTROL FOR UNMANNED AERIAL VEHICLES AND ROBOTIC SYSTEMS - A system is disclosed including an aerial vehicle to perform a task to an object, while in an aerial mode that includes at least one of a hover mode or a slow movement mode during a predominant phase of the task being performed, the aerial vehicle has a command and control system, a removable mobile computing device that when attached to the aerial vehicle assists in control of the aerial vehicle and when detached assists in control of the aerial vehicle with user intervention through the mobile device, wherein assist in control is further performed through the command and control system and at least one attachment attachable to the aerial vehicle for facilitating the task performed to the object by the aerial vehicle while the aerial vehicle is in the aerial mode, the at least one attachment is controlled by the removable mobile computing device. Methods are also disclosed. | 12-03-2015 |
20150344150 | DEVICE AND METHOD FOR CHECKING A LANDING GEAR SHOCK ABSORBER - The present invention relates to a device for checking a landing gear shock absorber. The device comprises first and second inclinometers. The first inclinometer is configured to measure the inclination of one of a slide, lower torque link and upper torque link of said shock absorber. The second inclinometer is configured to measure the inclination of another one of said slide, lower torque link and upper torque link. | 12-03-2015 |
20150346725 | UNMANNED VEHICLE OPERATING MODES - An aircraft is provided and includes a frame, drive elements configured to drive movements of the frame and a computer configured to receive mission planning and manual commands and to control operations of the drive elements to operate in a safe mode in which mission commands are accepted but manual commands are refused, a manual mode in which mission commands are refused but manual commands are accepted and an enroute mode. The computer is further configured to only allow mode transitions between the safe and manual modes and between the safe and enroute modes. | 12-03-2015 |
20150353190 | METHOD FOR MANAGING THE BRAKING OF AN AIRCRAFT WHEEL - Method for managing the braking of a wheel ( | 12-10-2015 |
20150353195 | Providing Services Using Unmanned Aerial Vehicles - Embodiments described herein may help to provide support via a fleet of unmanned aerial vehicles (UAVs). An illustrative medical-support system may include multiple UAVs, which are configured to provide support for a number of different situations. Further, the medical-support system may be configured to: (a) identify a remote situation, (b) determine a target location corresponding to the situation, (c) select a UAV from the fleet of UAVs, where the selection of the UAV is based on a determination that the selected UAV is configured for the identified situation, and (d) cause the selected UAV to travel to the target location to provide support. | 12-10-2015 |
20150360789 | METHOD AND DEVICE FOR CONTROLLING AT LEAST ONE ACTUATOR CONTROL SYSTEM OF AN AIRCRAFT, ASSOCIATED COMPUTER PROGRAM PRODUCT AND AIRCRAFT - A method and device for controlling at least one actuator control system of an aircraft, an associated computer program product and aircraft are disclosed. In one aspect, the method includes determining a variation in thrust of the aircraft for controlling a variable relating to the aircraft relative to a set point, calculating a first control command signal to be sent to an engine control system in order to obtain the variation in thrust, and transmitting the first control command signal to the engine control system. The controlled variable can be an acceleration along a direction taken by a speed vector among the air speed vector and the ground speed vector and the set point can be an acceleration set point along the direction. | 12-17-2015 |
20150361920 | OPTIMISING THE AVAILABILITY OF A THRUST REVERSER - A method of controlling a thrust reverser made up of a plurality of pieces of equipment, wherein, in the event of it being detected that one of the pieces of equipment has not activated by the end of a predetermined activation period, an error message relating to the malfunction of the thrust reverser is generated, and in spite of the error message being generated, activation of the equipment is continued, and if the equipment is finally activated before a predetermined maximum period for deployment of the thrust reverser, then deployment of the thrust reverser is continued and the error message relating to the malfunction of the thrust reverser is withdrawn. | 12-17-2015 |
20150364045 | METHOD AND DEVICE FOR DETERMINING A CONTROL SET POINT OF AN AIRCRAFT, ASSOCIATED COMPUTER PROGRAM AND AIRCRAFT - A method and device for determining a control set point of an aircraft, an associated computer program and an aircraft are disclosed. In one aspect, the method includes calculating a performance scale in the form of slope values of the aircraft, the performance scale including a slope characteristic value, the slope characteristic value being associated with a corresponding performance characteristic value. The method also includes acquiring a guidance set point and displaying the acquired guidance set point, in the form of a slope value with respect to the performance scale. The method further includes determining a slope characteristic value associated with a guidance set point displayed in the form of a slope value, and calculating an aircraft control set point, the control set point being calculated relative to the performance characteristic value corresponding to the determined slope characteristic value. | 12-17-2015 |
20150364046 | METHOD FOR PREDICTING A SHORT TERM FLIGHT PATH OF AN AIRCRAFT, COMPUTER PROGRAM PRODUCT, ASSOCIATED PREDICTION DEVICE, GUIDANCE METHOD, GUIDANCE SYSTEM AND AIRCRAFT - A method for predicting a short-term flight path of an aircraft, a computer program product, an associated prediction device, a guidance method, and a guidance system of an aircraft are disclosed. In one aspect, the flight path of the aircraft is associated at each time moment with a vector including at least one component from among a position of the aircraft, attitudes of the aircraft and order 1 and 2 time derivatives of the position and attitudes. The short-term flight path is the flight path of the aircraft for a time period of up to 30 seconds from a computation time of the flight path. The method includes acquiring a control signal representative of a displacement of a primary control member of the aircraft and predicting, at a subsequent prediction time, at least one component of the short-term flight path of the aircraft. The prediction step can be carried out at the computation time. | 12-17-2015 |
20150367933 | STRUT LENGTH AND PRESSURE REGULATION SYSTEM - A strut length and pressure regulation system is disclosed. The system may regulate the length of a strut by controlling the amount of gas in the strut. The system may monitor the length of the strut and/or pressure of gas in the strut and may change the amount of gas in the strut in response to the length of the strut and/or pressure of gas in the strut. In this manner, the effects of temperature changes may be compensated. | 12-24-2015 |
20150367950 | HYBRID TURBO ELECTRIC AERO-PROPULSION SYSTEM CONTROL - A control for a hybrid turbo electric aero-propulsion system prioritizes and optimizes the operating parameters, according to a desired optimization objective, for and across a number of different control optimization subsystems of the hybrid turbo electric aero-propulsion system. The control subsystems may include, for example, a propulsion control optimization subsystem and a power plant control optimization subsystem. The optimizations may be based on a system model, which is developed and updated during the operation of the hybrid turbo electric aero-propulsion system. | 12-24-2015 |
20150367951 | MONITOR SYSTEM FOR MONITORING THE STARTING OF A ROTARY WING AIRCRAFT, AN AIRCRAFT, AND A METHOD USING THE SYSTEM - A method of starting a turboshaft engine ( | 12-24-2015 |
20150370258 | METHOD FOR CONTROLLING A PATH OF A ROTARY-WING DRONE, A CORRESPONDING SYSTEM, A ROTARY-WING DRONE IMPLEMENTING THIS SYSTEM AND THE RELATED USES OF SUCH A DRONE - A method for controlling a path of a rotary-wing drone wherein said method comprises:
| 12-24-2015 |
20150371544 | METHOD AND DEVICE TO ESTIMATE COSTS OF DEVIATION IN A FLIGHT TRAJECTORY - A method and device for determining and presenting cost impacts generated by lateral route deviations of an aircraft. The device includes a computation unit for determining different flight trajectories, called alternative trajectories, each of which is offset laterally in the horizontal plane relative to a reference trajectory, notably the current trajectory of the aircraft, and a computation unit configured to compute, for each of the alternative trajectories, an associated overall cost which provides an indication of the cost generated by a flight of the aircraft along this alternative trajectory, the device also includes a display unit configured to present, on a navigation screen, indication elements which provide indications concerning the position and the associated overall cost for at least some of the alternative trajectories. | 12-24-2015 |
20150375857 | ACTIVE VIBRATION CONTROL DEVICES, SYSTEMS, AND METHODS - Improved active vibration control (AVC) devices ( | 12-31-2015 |
20150379874 | DYNAMIC SELECTION OF UNMANNED AERIAL VEHICLES - A device receives a request for a flight path from a first location to a second location in a region, and calculates the flight path based on the request and based on one or more of weather information, air traffic information, obstacle information, regulatory information, or historical information associated with the region. The device determines required capabilities for the flight path based on the request, and selects, from multiple UAVs, a particular UAV based on the required capabilities for the flight path and based on a ranking of the multiple UAVs. The device generates flight path instructions for the flight path, and provides the flight path instructions to the particular UAV to permit the particular UAV to travel from the first location to the second location via the flight path. | 12-31-2015 |
20160001877 | PASSIVE ROTOR CONTROL MECHANISM FOR MICRO AIR VEHICLES - Technology for achieving the behavior and benefits of traditional cyclic control in one rotor may be implemented with a simple under-actuated passive mechanism. An air vehicle employing the disclosed technology maintains lifting thrust by regulating the average rotor speed and generates control moments through coordinated pulsing of the motor torque. Rapid pulsing of the motor torque induces oscillations in propeller angle of attack, and so causes “cyclic control” without requiring the traditional auxiliary actuators and linkages. The MAV propulsion system is capable of using a minimum number of actuators in dual roles of thrust and moment objectives. | 01-07-2016 |
20160001880 | METHOD OF REGULATING THE SPEED OF ROTATION OF THE MAIN ROTOR OF A MULTI-ENGINED ROTORCRAFT IN THE EVENT OF ONE OF THE ENGINES FAILING - A method of regulating the speed of rotation of at least one main rotor of a multi-engined rotorcraft, which rotor is driven at variable speed. In the event of a failure of one of the main engines of the rotorcraft, a control unit generates an NR setpoint that is not less than the nominal drive speed (NRnom) of the main rotor. Thereafter, a calculator acts iteratively to determine a target speed (NRobj) for driving the main rotor to obtain stabilized lift of the rotorcraft by balancing between the torque developed by the main rotor and the rate of increase of its drive speed. The autopilot then causes the pitch of the blades of the main rotor to vary so as to obtain the iteratively calculated target speed (NRobj) until stabilized lift of the rotorcraft is obtained. | 01-07-2016 |
20160001894 | SKEW SENSING ARRANGEMENT - A skew detection system for a high lift system for an aircraft, wherein pairs of sensors | 01-07-2016 |
20160005319 | METHOD FOR ASSISTING THE PILOTING OF AN AIRCRAFT ON THE GROUND AND SYSTEM FOR ITS IMPLEMENTATION - A method for assisting the piloting of an aircraft on the ground comprises the steps of obtaining a panoramic view of at least one area adjacent to the aircraft, isolating an image corresponding to a part of the panoramic view and which is selected according to an orientation desired by the pilot, and displaying the image on a display device visible by the pilot. A system for the implementation of the method is also provided. | 01-07-2016 |
20160009404 | AUTONOMOUS PROPULSION APPARATUS AND METHODS | 01-14-2016 |
20160009408 | NITROGEN ENRICHED AIR SUPPLY SYSTEM AND AIRCRAFT | 01-14-2016 |
20160012736 | SMART ELECTRIC TAXI PATH CONTROL | 01-14-2016 |
20160016563 | ELECTRIC BRAKING SYSTEM AND METHOD RELYING ON VOLTAGE HYSTERESIS FOR APPLIED BRAKE POWER CONTROL - A method of operating electric brakes for a vehicle including monitoring at least a voltage in a power system of the vehicle, and adjusting a power provided to the electric brakes based on at least the monitored voltage to control a current according to a predetermined behavior. | 01-21-2016 |
20160016575 | DETERMINING INTEGRITY OF BRAKING CONTROL SYSTEM - A method of determining the integrity of an electric or hydraulic energy source of a braking control system. The energy source is charged or discharged, and two or more measurements of voltage or hydraulic pressure are taken from the braking control system. A difference between at least two of the measurements is determined in order to determine a change or rate of change in voltage or hydraulic pressure caused by the charging or discharging of the energy source. The integrity of the energy source is determined by checking whether the change or rate of change in voltage or hydraulic pressure meets predetermined criteria. The check may comprise comparing the change or rate of change of the voltage or hydraulic pressure to a threshold—for instance checking whether the change exceeds a threshold, or falls between an upper threshold and a lower threshold. | 01-21-2016 |
20160016576 | DETERMINING INTEGRITY OF BRAKING CONTROL SYSTEM - A method of determining the integrity of an electric or hydraulic braking control system. A reduction rate of a voltage or hydraulic pressure in the braking control system is determined, and the integrity of the braking control system is determined by comparing the reduction rate with a threshold. The braking control system may be an aircraft braking control system, and the method may be performed during flight of the aircraft—typically during cruise. | 01-21-2016 |
20160016655 | Input Congruence System for Flight Control Surfaces - A method and apparatus for controlling flight control surfaces on an aircraft. Commands are sent onto a data bus system from flight control modules. The flight control modules and actuator control modules determine whether an error is present in the commands sent onto the data bus system. Point-to-point connections between the flight control modules and the actuator control modules are managed based on whether the error is present in the commands sent onto the data bus system. | 01-21-2016 |
20160016660 | Force Command Update Rate Detection - The present disclosure relates to rate detection components, and more particularly, to a rate detection system that determines the update rate of commands. The update rate of the commands may be determined in response to the incidence of similarities and differences among samples of the commands. | 01-21-2016 |
20160016661 | DIFFERENTIAL BRAKING OF AIRCRAFT LANDING GEAR WHEELS - A method of braking left and right landing gear wheels on respective left and right sides of an aircraft. A desired left braking parameter (L) is received for the left wheel and a desired right braking parameter (R) is received for the right wheel. The left wheel is braked with a reduced left braking parameter (L′) which is less than the desired left braking parameter (L), and the right wheel is braked with a reduced right braking parameter (R′) which is less than the desired right braking parameter (R). A difference between the braking parameters is maintained so that L′−W=L−R. | 01-21-2016 |
20160016663 | Automotive Drone Deployment System - This disclosure generally relates to an automotive drone deployment system that includes at least a vehicle and a deployable drone that is configured to attach and detach from the vehicle. More specifically, the disclosure describes the vehicle and drone remaining in communication with each other to exchange information while the vehicle is being operated in an autonomous driving mode so that the vehicle's performance under the autonomous driving mode is enhanced. | 01-21-2016 |
20160017816 | Fuel Cutoff Testing System - A method and apparatus for controlling operation of an engine in an aircraft. A time when a cutoff speed for the aircraft will be reached at which a flow of fuel is to be stopped is identified. A delay between sending a command to move a switch to an off position and the time at which the engine ceases operation is also identified. The command is sent based on the predicted time and the delay. The command causes the switch to move to the off position moving a fuel control switch for the engine of the aircraft to a shut off position to stop the flow of fuel to the engine. | 01-21-2016 |
20160018793 | Control of aircraft systems with at least two remote data concentrators for control of an aircraft system component - A central processing unit for control of an aircraft system provided on board an aircraft, a control network for control of the aircraft system, an aircraft comprising such a control network, a corresponding method for control of the aircraft system and a computer program for carrying out the method. The central processing unit is connectable to at least two remote data concentrators over a network connection for control of a system component of an aircraft system. The central processing unit is configured to select one of the at least two remote data concentrators for control of the system component and to instruct the selected remote data concentrator to control the system component. | 01-21-2016 |
20160019797 | SCALAR PRODUCT BASED SPACING CALCULATION - A method is described that includes receiving, by a spacing system of an ownship aircraft, a current position of the ownship aircraft and a reference position of a target aircraft, wherein the reference position is a position of the target aircraft prior to a current position of the target aircraft. The method may also include, projecting, by the spacing system of the ownship aircraft, the reference position on a trajectory of the ownship aircraft, determining a first distance between the projected reference position and the current position, projecting, by the spacing system of the ownship aircraft, the current position on a trajectory of the reference position, determining a second distance between the projected current position and the reference position, and adjusting, by the spacing system and based on an average between the first distance and the second distance, a velocity of the ownship aircraft. | 01-21-2016 |
20160023757 | SYSTEM AND METHOD FOR AUTOMATION OF ROTORCRAFT ENTRY INTO AUTOROTATION AND MAINTENANCE OF STABILIZED AUTOROTATION - The system is configured for automation of rotorcraft entry into autorotation. The system can provide a means to assist the flight crew of a rotorcraft in maintaining rotor speed following loss of engine power. The system can automatically adjust control positions, actuator positions or both to prevent excessive loss of rotor speed upon initial loss of engine power before the flight crew is able to react. The system uses model matching to provide axis decoupling and yaw anticipation; it includes pitch control initially to assist in preventing rotor deceleration; and it makes use of collective, pitch, roll and yaw trim functions to provide tactile cueing to the pilot to assist when the pilot is in the loop. The system can reduce workload by assisting the crew with controlling rotor speed and forward speed during stabilized autorotation. | 01-28-2016 |
20160023762 | SYSTEMS AND METHODS FOR UAV DOCKING - Systems and methods are provided for docking an unmanned aerial vehicle (UAV) with a vehicle. The UAV may be able to distinguish a companion vehicle from other vehicles in the area and vice versa. The UAV may take off and/or land on the vehicle. The UAV may be used to capture images and stream the images live to a display within the vehicle. The vehicle may control the UAV. The UAV may be in communication with the companion vehicle while in flight. | 01-28-2016 |
20160025457 | MULTIMODE UNMANNED AERIAL VEHICLE - A system comprising an unmanned aerial vehicle (UAV) configured to transition from a terminal homing mode to a target search mode, responsive to an uplink signal and/or an autonomous determination of scene change. | 01-28-2016 |
20160025495 | AUTONOMOUS COORDINATION OF AGENTS VIA ATTRACTION AND REPULSION - A method of controlling movement of an agent operating within an autonomous system includes determining, using a processing device associated with the agent, at least one point of interest (POI) within an area of operation by the autonomous system; determining, from the at least one POI, a POI of highest attraction for the agent and calculating an attraction force for the agent, based on the location of the POI of highest attraction; determining proximity of the agent to one or more additional agents operating within the autonomous system, and calculating a repulsion force for the agent so as to maintain a minimum separating distance between the agent and the one or more additional agents; calculating a resultant force for the agent based on the attraction force and the repulsion force; and changing a direction of the agent based on the resultant force. | 01-28-2016 |
20160027311 | METHODS AND SYSTEMS FOR WIND MITIGATION IN AUTONOMOUS PARAFOIL GUIDANCE - According to one aspect, a flight controller constructed to control a parafoil in flight from a starting location to a target location is provided. The flight controller includes an interface constructed to connect to one or more actuators and one or more wind sensors, a memory, a processor coupled to the memory, the interface, and a flight manager component executable by the processor. The flight manager component is configured to identify the target location and the starting location, receive wind data, determine a relationship between a ground reference frame (GRF) and a wind fixed frame (WFF) based on the wind data, generate a trajectory between the starting location and the target location in the WFF, determine a desired heading based on the trajectory and the relationship between the GRF and the WFF, and generate an actuator control signal based on the desired heading to adjust a heading of the parafoil. | 01-28-2016 |
20160031547 | Electronic Stopper in Actuator Control - A system and method of controlling a position of a structure. A position command indicating a desired position for the structure and a position feedback signal indicating the position of the structure are received. A position control signal is generated based on a difference between the desired position and the position indicated by the position feedback signal. A stop feedback signal relative to the position of the structure is received. A stop control signal is generated based on the stop feedback signal and a stop condition for the structure. One of the position control signal and the stop control signal is selected. The selected one of the position control signal and the stop control signal is provided to an actuator for controlling the position of the structure. | 02-04-2016 |
20160031552 | SYSTEMS AND METHODS FOR AIRCRAFT BRAKE SENSORS - An aircraft brake system may include a linear variable differential transformer (“LVDT”). A brake control unit (“BCU”) may measure an output voltage from the LVDT. The BCU may include a hardware module, a software module, and an offset module. The hardware module may include a preprogrammed threshold voltage. The output voltage may be measured, and an offset voltage may be determined and stored in the offset module. The software module may measure the sum of the output voltage and the offset voltage. In response to the hardware module and the software module indicating that the threshold voltage has been reached, the BCU may allow braking of the aircraft. | 02-04-2016 |
20160031553 | ELECTRIC BRAKING SYSTEM WITH POWER CONSERVATION AND METHOD OF OPERATING THE SAME - A method of operating electric brakes ( | 02-04-2016 |
20160031565 | SYSTEMS AND METHODS FOR AVERTING OVERWEIGHT AIRCRAFT LANDING CIRCUMSTANCES - The present disclosure includes a method, article of manufacture, and system for averting an overweight landing of an aircraft having a maximum landing weight (MLW). The method, article, and system may comprise, mutatis mutandis, determining a flight plan, receiving sensor data, determining, in response to the sensor data, that a predetermined event has occurred, receiving, in response to the predetermined event, an updated destination, computing, aircraft weight at the updated destination (WAD), comparing the WAD to the MLW, and/or generating, in response to the sensor data, an updated flight plan when the WAD exceeds the MLW. | 02-04-2016 |
20160039396 | INDEPENDENT BRAKE CONTROL OF A COMMON AIRCRAFT GEAR - A brake control system for a landing gear of an aircraft is provided. The system includes a first control channel for providing brake control signals to one or more brakes on the landing gear, and a second control channel for providing brake control signals to another one or more brakes on the landing gear. At least one of the first control channel and the second control channel is configured to act as an executive in monitoring braking efforts applied by the one or more brakes as compared to braking efforts applied by the another one or more brake, and to cause the braking efforts of at least one of the one or more brakes or the another one or more brakes to be modified in an effort to equalize the braking efforts. | 02-11-2016 |
20160042637 | Drone Safety Alert Monitoring System and Method - A wearable safety alarm system includes one or more processors to receive identifying information and transmit the identifying information to an alarm response server from a mobile computing device, receive, by the mobile computing device, a unique identifier that identifies the identifying information in database associated with the alarm response server, receive a trigger of an alarm notification by one of a wearable device and the mobile computing device, determine a current location of the mobile computing device, transmit an alarm notification message to the alarm response server, the alarm notification message including the current location of the mobile computing device and the unique identifier, and transmit the current location of the mobile computing device to at least one drone. | 02-11-2016 |
20160046367 | HELICOPTER VIBRATION CONTROL SYSTEM AND CIRCULAR FORCE GENERATION SYSTEMS FOR CANCELING VIBRATIONS - A rotary wing aircraft including a vehicle vibration control system. The vehicle vibration control system includes a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to the relative rotation of the rotating rotary wing hub member rotating relative to the body, at least a first nonrotating body vibration sensor, the at least first nonrotating body vibration sensor outputting at least first nonrotating body vibration sensor data correlating to vibrations, at least a first nonrotating body circular force generator, the at least a first nonrotating body circular force generator fixedly coupled with the nonrotating body, the at least first nonrotating body circular force generator controlled to produce a rotating force with a controllable rotating force magnitude and a controllable rotating force phase, the controllable rotating force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with the controllable rotating force phase controlled in reference to the rotary wing aircraft member sensor data correlating to the relative rotation of the rotating rotary wing hub rotating relative to the nonrotating body wherein the vibration sensed by the at least first nonrotating body vibration sensor is reduced. | 02-18-2016 |
20160046376 | APPARATUS AND METHOD FOR ALLOWING MULTI-MODE USE OF AN AIRCRAFT COCKPIT - In one embodiment, multi-mode use of an aircraft cockpit is realized a processor in the aircraft determining whether the aircraft is operating in a flight mode or a non-flight mode. When operating in the non-flight mode, the processor deactivates aircraft engines and permits wireless device access to one or more aircraft systems. When operating in the flight mode, the processor enables aircraft engines and prevents wireless device access to one or more aircraft systems. | 02-18-2016 |
20160046382 | DUAL DISSIMILAR ENGINES FOR AN AIRCRAFT - A system and method for controlling a tail-sitter aircraft, includes determining a mode of operation for the aircraft; operating each of a large turbine engine and a small turbine engine to provide total aircraft power during hover or high-power mode of operation; and selectively providing aircraft power from the small turbine engine to a plurality of rotors during a long-range endurance cruise mode of operation. | 02-18-2016 |
20160049021 | AIRCRAFT ELECTRONIC FINGERPRINT AND MONITORING PERFORMANCE OF AN AIRCRAFT COMPONENT USING THE AIRCRAFT'S ELECTRONIC FINGERPRINT - An initial electronic fingerprint for a vehicle and selected component of the vehicle, e.g. an aircraft windshield having a heatable member, is made. During operation of the aircraft, the initial electronic fingerprint of the aircraft and a real time electronic fingerprint of the aircraft are compared to determine the operating performance of the heatable member. The parameter that provides the performance of the component includes a time count within a predetermined time period. As the time count increases during the predetermined time period, the performance of the heatable member toward unacceptable performance increases. | 02-18-2016 |
20160050840 | METHODS FOR AGRONOMIC AND AGRICULTURAL MONITORING USING UNMANNED AERIAL SYSTEMS - A method for agronomic and agricultural monitoring includes designating an area for imaging, determining a flight path above the designated area, operating an unmanned aerial vehicle (UAV) along the flight path, acquiring images of the area using a camera system attached to the UAV, and processing the acquired images. | 02-25-2016 |
20160052138 | SYSTEMS, DEVICES, AND METHODS INCLUDING A WHEELCHAIR-ASSIST ROBOT - Systems, devices, and methods are described for providing, among other things, a wheelchair-assist robot for assisting a wheelchair user with everyday tasks or activities at work, at home, and the like. In an embodiment, the mobile wheelchair-assist robot includes a wheelchair interface component configured to exchange control information with a wheelchair controller. In an embodiment, a wheelchair-assist robot mount assembly is provided for, among other things, electrically and physically coupling a wheelchair-assist robot to an associated wheelchair. | 02-25-2016 |
20160052642 | AIRCRAFT ELECTRIC TAXI HEALTH MANAGEMENT SYSTEM AND METHOD - An aircraft electric taxi health management system includes a right electric motor drivingly connected to at least one wheel on a right landing gear assembly, a left electric motor drivingly connected to at least one wheel on a left landing gear assembly, a right motor controller configured to electrically drive the right electric motor, monitor the right motor current and voltage, and generate right motor signals as a function of the right motor current and voltage; a left motor controller configured to electrically drive the left electric motor, monitor the left motor current and voltage, and generate left motor signals as a function of the left motor current and voltage; and a health management controller configured to compare the right motor signals to the left motor signals; and generate electric taxi system maintenance signals based on the comparison. | 02-25-2016 |
20160054737 | Methods and Apparatus for Unmanned Aerial Vehicle Autonomous Aviation - In some embodiments, an Unmanned Aerial Vehicle (UAV) is configured to navigate to a first location point from a plurality of location points. The plurality of location points defines a flight pattern. The UAV is further configured to receive a set of location coordinates of a moving object. The UAV is configured to determine the distance between the moving object and the UAV based on the set of location coordinates of the moving object and the first location point of the UAV. When the distance between the moving object and the UAV reaches a pre-determined threshold, the UAV is configured to advance to a second location point from the plurality of location points. | 02-25-2016 |
20160055753 | SYSTEM AND METHOD FOR MAXIMIZING DISPLAYING OF TRAJECTORY ELEMENTS IN AN EDIT AREA OF A NAVIGATIONAL DISPLAY OF A COCKPIT DISPLAY SYSTEM - A system and method for maximizing displaying of trajectory elements in an edit area of a navigational display are disclosed. In one embodiment, navigational display parameters are obtained from a cockpit display system. Further, flight plan information is obtained from a flight management system (FMS). Furthermore, a portion of the flight plan information which lies within the edit area of the navigation display is dynamically determined using the navigational display parameters. In addition, a display buffer is dynamically populated with only the determined portion of the flight plan information. Moreover, any needed data that is in the determined portion of the flight plan information is dynamically refreshed in the display buffer. Also, the flight plan information is dynamically displayed on the edit area of the navigation display using the refreshed and populated flight plan information and the needed data. | 02-25-2016 |
20160059953 | SYSTEM AND A METHOD OF OPERATION OF THE SYSTEM INCORPORATING A GRAPHICAL USER INTERFACE IN A BULKHEAD OF A VEHICLE CABIN - A method of operation for a system incorporating a graphical user interface disposed in a bulkhead within a cabin of an aircraft. The method includes displaying a menu for at least one controllable parameter, receiving a selection of the controllable parameter, displaying at least one control for the selected controllable parameter, receiving a control input for the selected controllable parameter, and adjusting the selected controllable parameter consistent with the control input. The controllable parameter may be one from a plurality of controllable parameters selected from a group that includes cabin light intensity, cabin light color, temperature, and the degree of openness of at least one window shade. A system and an executable computer program product also are provided. | 03-03-2016 |
20160059954 | SYSTEM AND A METHOD OF OPERATION OF THE SYSTEM INCORPORATING A GRAPHICAL USER INTERFACE ON A MOBILE COMPUTING DEVICE FOR A PASSENGER IN A VEHICLE CABIN - A method of operation for a system incorporating a graphical user interface in a mobile computing device for a passenger within a cabin of an aircraft. The method includes displaying a menu for at least one controllable parameter, receiving a selection of the controllable parameter, displaying at least one control for the selected controllable parameter, receiving a control input for the selected controllable parameter, and adjusting the selected controllable parameter consistent with the control input. The controllable parameter include a plurality of controllable parameters selected from a group encompassing light intensity, light color, temperature, and the degree of openness of at least one window shade. A system and executable computer program product also are provided. | 03-03-2016 |
20160059958 | Controlling Rotary Wing Aircraft - A rotary wing aircraft can include a central body and at least three rotors, each rotor connected to the central body by a swashplate. A system for controlling the flight of an aircraft with a plurality of rotors can include: an electronic control system programmed to calculate a pitch for blades of each rotor of the plurality of rotors based on an input indicating a desired motion of the aircraft; and a plurality of swashplates, each swashplate associated with a unique rotor of the plurality of rotors, each swash plate in electronic communication with the electronic control system and operable to control the pitch for blades of the associated unique rotor in response to signals from the electronic control system. | 03-03-2016 |
20160059962 | UNMANNED AERIAL VEHICLE FOR HAZARD DETECTION - In an approach to hazard detection, one or more computer processors determine whether an obstruction of view for a user in a first vehicle is detected. Responsive to determining the obstruction is detected, the one or more computer processors deploy a first unmanned aerial vehicle (UAV) associated with the first vehicle. The one or more computer processors determine whether one or more hazards associated with a path of the first vehicle are detected. | 03-03-2016 |
20160063869 | SYSTEM AND METHOD FOR DISPLAYING TRAFFIC AND ASSOCIATED ALERTS ON A THREE-DIMENSIONAL AIRPORT MOVING MAP DISPLAY - A flight deck display system and method comprises a first source of host aircraft feature data and a second source of traffic data. A processor is coupled to the first and second sources and is configured to (a) receive host aircraft data; (2) receive traffic data; (3) filter traffic based on a predetermined set of separation criteria to identify vital traffic; (4) generate symbology graphically representative of vital traffic; (5) generate symbology graphically representative of the host aircraft; and (6) display the host aircraft and the vital traffic on an AMM display. | 03-03-2016 |
20160063870 | SYSTEM FOR TESTING OF AUTONOMY IN COMPLEX ENVIRONMENTS - A monitoring apparatus for deployment on an AUV may include navigation equipment operable independent of guidance and control equipment of the AUV and usable for determining AUV navigation information during deployment of the AUV, radio equipment operable independent of a radio module of the AUV and for providing a communication link to a ground station for communication with testing staff, and a watchdog module comprising processing circuitry configured to monitor at least the AUV navigation information relative to operational guidance to determine whether a constraint defined in the operational guidance is violated. | 03-03-2016 |
20160068256 | FAULT TOLERANT ELECTRONIC CONTROL ARCHITECTURE FOR AIRCRAFT ACTUATION SYSTEM - An electronic control architecture for an aircraft actuation system may include a first channel and a second channel. The first channel may be configured to receive one or more inputs comprising a movement command, to produce an output to control a component of the system, and to receive feedback from the component respective of movement of the component. The first channel may comprise a fault detection module configured to compare the feedback to the command to determine if the first channel is functioning properly. The second channel may be configured to receive the one or more inputs and, if the first channel is not functioning properly, to produce an output to control the component. | 03-10-2016 |
20160068265 | PACKAGE TRANSPORT BY UNMANNED AERIAL VEHICLES - According to an aspect, an unmanned aerial vehicle (UAV) is provided that is capable of flying between a pick up point and a delivery point with respect to a package transfer operation. The delivery point is identifiable by the UAV through global positioning system (GPS) coordinates of the delivery point and verification of a device identifier of a package docking device (PDD) associated with a package transfer request. A control processor coupled to the UAV receives a transaction packet for the operation that includes the GPS coordinates and the device identifier of the PDD associated with the request. Upon arrival of the UAV at the delivery point, the control processor verifies that a device identifier of a PDD located at the delivery point matches the device identifier in the transaction packet, implements the package transfer operation, and transmits confirmation of completion of the operation to an originator of the request. | 03-10-2016 |
20160068268 | GOAL-BASED PLANNING SYSTEM - A method and apparatus for determining actions for entities ( | 03-10-2016 |
20160069688 | SYSTEM AND METHOD FOR MANAGING SPEED CONSTRAINTS DURING REQUIRED TIME OF ARRIVAL OPERATIONS - A method and apparatus includes strategies for improving required time of arrival reliability by an aircraft comprising determining a speed correction for one of AT speed constraints or an AT or ABOVE speed constraints, wherein the determining is selected from one or more of the mechanisms from the group consisting of continuous RTA speed management between constraints, padding of the AT speed constraints and the AT or ABOVE speed constraints; decelerating proactively; and using a variable guidance margin, wherein the guidance margin is a speed change not reflected in a flight plan prediction. | 03-10-2016 |
20160070260 | UNMANNED DEVICE UTILIZATION METHODS AND SYSTEMS - Structures and protocols are presented for configuring an unmanned aerial device to perform a task, alone or in combination with other entities, or for using data resulting from such a configuration or performance. | 03-10-2016 |
20160070265 | MULTI-SENSOR ENVIRONMENTAL MAPPING - Systems and methods for controlling a movable object within an environment are provided. In one aspect, a method may comprise: determining, using at least one of a plurality of sensors carried by the movable object, an initial location of the movable object; generating a first signal to cause the movable object to navigate within the environment; receiving, using the at least one of the plurality of sensors, sensing data pertaining to the environment; generating, based on the sensing data, an environmental map representative of at least a portion of the environment; receiving an instruction to return to the initial location; and generating a second signal to cause the movable object to return to the initial location, based on the environmental map. | 03-10-2016 |
20160076892 | METHODS AND SYSTEMS FOR DETERMINING A STATE OF AN UNMANNED AERIAL VEHICLE - The present invention provides methods and systems related to determine a state of the UAV by updating a determined state of UAV with a relative proportional relationship. The UAV may be provided with a monocular camera, a proximity sensor and a processor. The processor may determine external state information of the UAV based on image data captured by the monocular camera, and calculate a relative proportional relationship to be applied to the determined external state information. The updated external state information of the UAV may be more precise or even equal to the actual state information of the UAV, thus enabling more accurate control and navigation for the autonomous flight. | 03-17-2016 |
20160078759 | Tracking a Vehicle Using an Unmanned Aerial Vehicle - Tracking a vehicle using an unmanned aerial vehicle is disclosed. One or more first images may be received from a first camera of the first unmanned aerial vehicle located at a first location. A unique identifier of a first vehicle may be determined to be not identifiable in at least one of the one or more first images. The first unmanned aerial vehicle may be then repositioned. One or more second images having the second field of view and showing the first vehicle may then be received. The unique identifier of the first vehicle may then be determined based on at least one of the one or more second images. | 03-17-2016 |
20160078770 | MAN-MACHINE INTERFACE FOR THE MANAGEMENT OF THE TRAJECTORY OF AN AIRCRAFT - A method of graphical manipulation of the trajectory of an aircraft comprises the steps of receiving an indication of a deformation point associated with the trajectory of the aircraft; determining a zone of local modification of the trajectory of the aircraft as a function of the deformation point; computing a modified trajectory and graphically restoring the modified trajectory. A parameter associated with the indication of the deformation point, notably a speed and/or acceleration value (for example of the contact point on the touch-sensitive interface, or else of a cursor), is received or determined. A modified trajectory is computed by selecting a computation algorithm from among a plurality of faster or slower predefined algorithms; the selection being performed as a function of the parameter. Various other developments are described (configurable selection, trajectory modification bounds, processing of an arbitrary deformation point, i.e. one other than a point of the flight plan, etc.). | 03-17-2016 |
20160083085 | ELECTRIFIED ROTORCRAFT - An electrified propulsion system for a rotary wing aircraft includes a flight control computer that receives a signal indicative of a power demand on an engine; an engine control system that is in communication with the engine and is configured to control operation of the engine at a selected operating point; a generator that is in mechanical communication with the engine and is configured to receive mechanical power from the engine and convert the mechanical power to electrical power; an electric motor that is in electrical communication with the generator and is configured to receive the electric power; and a rotor that is in mechanical communication with the electric motor; wherein the electric motor is configured to control rotation and provide the mechanical power demand of the rotor at the selected operating point in response to the received signal. | 03-24-2016 |
20160083104 | SUPPLEMENTAL POWER FOR REDUCTION OF PRIME MOVER - Embodiments are directed to selecting, by a computing device comprising a processor, the size of at least one prime mover associated with an aircraft to satisfy a baseline power requirement for operation of the aircraft during a steady state load condition, selecting at least one power source configuration to supplement power provided by the at least one prime mover during a transient load condition associated with the operation of the aircraft, and selecting, by the computing device, a parameter of the at least one power source configuration to provide a total power in an amount that is greater than a threshold during the transient condition. | 03-24-2016 |
20160083115 | APPARATUS AND METHODS FOR TETHERED AERIAL PLATFORM AND SYSTEM - A drone system includes a drone that includes a propulsion system, a flight stabilizer system, and an air payload interface unit, and a camera system, wherein the camera system includes a camera stabilizing unit, and a ground support system to which the drone is detachably coupled through a tether unit, and for providing electrical power to the propulsion system. The drone system further includes a ground payload interface unit for receiving and transmitting command and telemetry information to the air payload interface unit through the tether unit, and a controlling device for controlling the propulsion system and the camera system through the tether unit. | 03-24-2016 |
20160086494 | Method and Apparatus for Ensuring the Operation and Integrity of a Three-Dimensional Integrated Logistical System - A method for ensuring the operation and integrity of a three-dimensional integrated logistical system that includes a plurality of drones and a plurality of service stations; each of the plurality of drones having a plurality of environmental sensors and a plurality of internal sensors. The plurality of drones is routed to a destination location through a fleet management software that monitors the plurality of drones and the plurality of service stations. The fleet management software is able to detect operational issues amongst the plurality of drones and if necessary reroute the plurality of drones to the plurality of service stations in order to resolve said operational issues. A robotic service unit in each of the plurality of service stations is able to autonomously service the plurality of drones in addition to equipping the plurality of drones with a designated payload. | 03-24-2016 |
20160090170 | INTERFACE FOR CONTROL OF A FOLDABLE WING ON AN AIRCRAFT - An aircraft comprises a foldable wing, the wing comprising an inner region and an outer region, such as a wing tip. The outer region is moveable relative to the inner region between a flight configuration and a ground configuration in which the span is reduced. The aircraft comprises a control system and a control interface. The control interface comprises a selector for selecting the desired configuration of the outer region, and is arrange to provide: a first output, such as a light, when the flight configuration is selected and the outer region is in the flight configuration; a second output, such an amber light, when the ground configuration is selected and the outer region is in the ground configuration; and a third output, such as a red light, when the outer region is not in the selected configuration. | 03-31-2016 |
20160090186 | INTELLIGENT INTEGRATED PROPULSION CONTROL SYSTEM AND METHOD - Control systems and methods for a propulsion system are disclosed in which the propulsion control system is integrated to intelligently control propulsion and minimize transient effects from the power demands of other subsystems. | 03-31-2016 |
20160090194 | SYSTEMS AND METHODS FOR PROVIDING VISUAL FEEDBACK IN AIRCRAFT - A system for providing visual feedback in an aircraft having an actuatable component includes a controller providing automatic control of the actuatable component in an automatic mode and permitting manual control of the actuatable component in a manual mode. A handle assembly is in communication with the actuatable component to provide manual control of the actuatable component in the manual mode. The system also includes a light panel integrated with the handle assembly, in communication with said controller, and configured to selectively illuminate to inform a user of the mode of the actuatable component. | 03-31-2016 |
20160093223 | Unknown - A method implemented by computer for the management of the flight of an aircraft comprises the steps of receiving flight directives and flight information associated with these directives; determining a flight context of the aircraft; as a function of the context determined, selecting information from among that associated with the formulation of a directive and/or with a current flight directive and/or with a change of a flight directive; sensorially restoring the selected information. Various developments are described, notably links to documentary resources, the determination of anomalies, the use of predefined logic rules and configuration options. System aspects and software aspects are described. | 03-31-2016 |
20160096616 | METHODS AND APPARATUS FOR PROVIDING SERVO TORQUE CONTROL WITH LOAD COMPENSATION FOR PILOT IN THE LOOP - A method for operating a mechanical flight control system is provided. The method provides a torque command to a servo torque control loop, wherein the servo torque control loop comprises at least one position control servo; receives at least one feedback signal from the position control servo, during operation of the position control servo; detects user external load disturbance input to the servo torque control loop, based on the at least one feedback signal; and adjusts operation of the position control servo, based on the detected user external load disturbance input. | 04-07-2016 |
20160097621 | MULTI-HYPOTHESIS FIRE CONTROL AND GUIDANCE - This disclosure provides systems, methods, and apparatus for intercepting a moving target by a plurality of interceptors that individually have insufficient capability to achieve intercept. An electronic processor can receive information corresponding to a state of the moving target at a first time. The electronic processor can determine a plurality of hypotheses for the future maneuvers of the moving target. The hypotheses can be based in part on the state of the moving target at the first time and the location of any defended assets. The electronic processor can assign a respective target maneuver hypothesis or set of hypotheses to each of a plurality of interceptors. The electronic processor can assign firing times and/or initial guidance commands to each interceptor. The electronic processor can update the set of feasible hypotheses based on additional receipt of information on the motion of the target and communicate this information to interceptors in flight via a communication subsystem. The electronic processor, or a secondary electronic processor located on each interceptor, can control each interceptor to maneuver such that the moving target is intercepted, based on the respective target maneuver hypotheses. | 04-07-2016 |
20160101870 | METHOD OF REGULATING THE SPEED AT WHICH A ROTORCRAFT ROTOR IS DRIVEN UNDER ICING CONDITIONS - A method of regulating the NR speed at which the rotor of a rotorcraft is driven in rotation. On detecting that the rotorcraft is flying under icing conditions in a previously identified critical temperature domain (Dct), the NR speed is either decreased in the situation where the ambient outside air temperature (OAT) lies in a low temperature icing range (Ptb) of the critical temperature domain (Dct), or else it is increased in the situation where the ambient outside air temperature (OAT) lies within a high temperature icing range (Pth) of the critical temperature domain (Dct). | 04-14-2016 |
20160101872 | SYSTEMS AND METHODS FOR FUEL MONITORING - A zero fuel time is determined and presented to an operator of an unmanned aerial vehicle (UAV). Zero fuel time may be determined based on a fuel burn rate and an amount of remaining fuel. A return to base time is determined and presented to an operator of a UAV. Return to base time may be determined based on a location of the UAV and a location of a base. Zero fuel time and return to base time are presented to an operator of a UAV proximate to one another using contrasting and/or varying visual characteristics to ease comparison and identification of this data. | 04-14-2016 |
20160101873 | PILOT ASSISTANCE SYSTEM OF AN AIRCRAFT - The present invention relates to an aid system ( | 04-14-2016 |
20160102625 | System and Method for Alerting and Suppression of Detonation and/or Pre Ignition Phenomena in Internal Combustion Engines by Monitoring RPM Fluctuation - An engine system with advance detection of detonation and/or pre ignition, the system comprising an engine, operative for propulsion of a vehicle by generating rotational motion, whose rotational velocity over time is monitored; and a detonation and/or pre ignition detector operative to provide an alert for impending detonation and/or pre ignition of the engine, if the rotational velocity fluctuates over time to an extent which is predetermined to be unsafe. | 04-14-2016 |
20160107539 | ELECTRIC VEHICLE TRACTION CONTROL SYSTEM AND METHOD - A traction control system and method are provided for electric vehicles with at least one drive wheel powered by an electric drive motor to maintain optimum maximum traction while the vehicle is driven on the ground. The traction control system includes drive means capable of transmitting torque through a vehicle drive wheel and controllable to move the vehicle over a ground surface. A preferred drive means is an electric motor designed to move the vehicle at desired ground speeds in response to operator input. Operator input requests a desired speed, and the system determines drive wheel torque required to produce the desired speed and provides maximum current to produce maximum torque to drive the vehicle with optimum traction at the desired speed. The system uses constant feedback to find maximum current corresponding to torque required for an inputted speed request to automatically control traction in any electric powered vehicle. | 04-21-2016 |
20160107749 | Fixed Drone Visualization In Security Systems - An unmanned aerial vehicle is described and includes a computer carried by the unmanned aerial vehicle to control flight of the unmanned aerial vehicle and at least one sensor. The unmanned aerial vehicle is caused to fly to a specific location within a facility, where the unmanned aerial vehicle enters a hover mode, where the unmanned aerial vehicle remains in a substantially fixed location hovering over the specific location within the facility and sends raw or processing results of sensor data from the sensor to a remote server system. | 04-21-2016 |
20160107759 | METHOD OF DRIVING ROTATION OF A ROTORCRAFT ROTOR BY ANTICIPATING TORQUE NEEDS BETWEEN TWO ROTARY SPEED SETPOINTS OF THE ROTOR - A method of driving a rotorcraft rotor ( | 04-21-2016 |
20160107762 | METHOD AND DEVICE FOR AUTOMATICALLY ESTIMATING AT LEAST ONE SPEED OF AN AIRCRAFT - A device including a first data generating unit for determining at least one aerodynamic hinge moment of at least one control surface of the aircraft, a second data generating unit for determining a plurality of data and at least one external static pressure and a model of hinge moment coefficient, a computation unit for computing with the aid of these data at least one speed of the aircraft, namely a Mach number and/or a conventional speed, and a data transmission unit for providing this speed to a user system. | 04-21-2016 |
20160109882 | AIRCRAFT SIDESTICK PRIORITY AND DUAL INPUT CONTROL LOGIC - The present invention relates to a fly-by-wire type of aircraft flight control system having a pair of sidesticks for pilot and co-pilot input, respectively, and having logic that controls the priority of input as between the two sidesticks in certain aircraft flight situations. It allows either the pilot or co-pilot to ensure that his/her sidestick is the only one issuing flight control commands at any one moment in time by first pressing a simple latch button located, for example, on the glareshield in the cockpit and then maneuvering the sidestick in the desired manner to effectuate flight control, e.g., pitch and/or roll, of the aircraft. | 04-21-2016 |
20160111006 | USER INTERFACES FOR SELECTING UNMANNED AERIAL VEHICLES AND MISSION PLANS FOR UNMANNED AERIAL VEHICLES - A device receives a request for a mission that includes traversal of a flight path and performance of mission operations, and presents a first user interface that requests mission information. The device receives the mission information, and determines recommended UAVs for the mission based on the mission information. The device presents information associated with the recommended UAVs, and receives a selection of a particular UAV via the first user interface. The device determines recommended mission plans based on the mission information and the particular UAV, and presents the recommended mission plans via a second user interface. The device receives a selection of a particular mission plan via the second user interface, and generates mission plan instructions for the particular mission plan. The device provides the mission plan instructions to the particular UAV to permit the particular UAV to travel the flight path and perform the mission operations. | 04-21-2016 |
20160114881 | METHOD FOR DETERMINING A STATE OF A COMPONENT IN A HIGH LIFT SYSTEM OF AN AIRCRAFT, HIGH LIFT SYSTEM OF AN AIRCRAFT AND AIRCRAFT HAVING SUCH A HIGH LIFT SYSTEM - A method for determining a state of a component in a high lift system of an aircraft, the high lift system including a central power control unit for providing rotational power by a transmission shaft; and drive stations coupled with the power control unit and movable high lift surfaces, includes acquiring in an extended position in flight a first position of a first position pick-off unit coupled with the component, mechanically coupled with a high lift surface, and coupled with a drive station; acquiring in flight a second position of a second position pick-off unit arranged in or at the central power control unit in the extended position; determining a deviation between a first measure based on the first position and a second measure based on the second position; determining, whether the deviation exceeds a predetermined threshold; and if so, generating a signal indicating an abnormal state of the component. | 04-28-2016 |
20160114882 | FLY-BY-WIRE FLIGHT CONTROL SYSTEM AND METHOD - A multi-axis serially redundant, single channel, multi-path fly-by-wire control system comprising: serially redundant flight control computers in a single channel where only one “primary” flight control computer is active and controlling at any given time; a matrix of parallel flight control surface controllers including stabilizer motor control units (SMCU) and actuator electronics control modules (AECM) define multiple control paths within the single channel, each implemented with dissimilar hardware and which each control the movement of a distributed set of flight control surfaces on the aircraft in response to flight control surface commands of the primary flight control computer; and a set of (pilot and co-pilot) controls and aircraft surface/reference/navigation sensors and systems which provide input to a primary flight control computer and are used to generate the flight control surface commands to control the aircraft in flight in accordance with the control law algorithms implemented in the flight control computers. | 04-28-2016 |
20160114900 | System and Method for Cruise Monitoring and Alerting - A monitoring system is disclosed for use with a mobile platform being operated by an operator. The system may make use of a database for containing operational information and procedures relating to the operation of the mobile platform by the operator. A processor may also be used that communicates with the database and with at least one subsystem of the mobile platform for monitoring operational information concerning operation of the mobile platform against stored information contained in the database. The processor may determine if the operation of the mobile platform is proceeding in accordance with predetermined standards. | 04-28-2016 |
20160114903 | FLIGHT ENVELOPE PROTECTION SYSTEM FOR UNMANNED AERIAL VEHICLES - Systems and methods to protect the flight envelope in both manual flight and flight by a commercial autopilot are provided. A system can comprise: an inertial measurement unit (IMU); a computing device in data communication with the IMU; an application executable by the computing device comprising: logic that estimates an angle of attack; a slip angle; and a speed of an unmanned aerial vehicle (UAV) based at least in part on data received from the UAV. A method can comprise estimating, via a computing device, flight data of a UAV based at least in part on data received from an IMU; comparing the estimated flight data with measured flight data; and triggering an error indication in response to a determination that the measured flight data exceeds a predefined deviation of the estimated flight data. The estimated speed can comprise an estimated airspeed, vertical speed and/or ground velocity. | 04-28-2016 |
20160114904 | METHOD FOR DETERMINING A STATE OF A COMPONENT IN A HIGH LIFT SYSTEM OF AN AIRCRAFT, HIGH LIFT SYSTEM OF AN AIRCRAFT, AND AIRCRAFT HAVING SUCH A HIGH LIFT SYSTEM - A method for determining a state of a component in a high lift system of an aircraft is proposed, the high lift system comprising a central power control unit for providing rotational power by means of a transmission shaft; and drive stations coupled with the power control unit and movable high lift surfaces. | 04-28-2016 |
20160116915 | SURVEYING AREAS USING A RADAR SYSTEM AND AN UNMANNED AERIAL VEHICLE - System and methods for surveying areas using a radar system and an unmanned aerial vehicle (UAV) are described herein. For example, one or more embodiments include detecting an event in the area using movement measurements from a radar system, wherein the radar system transmits electromagnetic radiation waves to capture the movement measurements in the area, and determining geographic information system (GIS) coordinates of a location of the event. Further, one or more embodiments can include navigating an UAV to the location substantially autonomously using the GIS coordinates of the location of the event and capturing a second number of images of the location using the UAV. | 04-28-2016 |
20160117929 | SYSTEM AND METHOD FOR OPERATION OF UNMANNED AIRCRAFT WITHIN A MANAGED AIRSPACE OR FLYWAY - A system and method for management of airspace for unmanned aircraft is disclosed. The system and method comprises administration of the airspace including designation of flyways and zones with reference to features in the region. The system and method comprises administration of aircraft including registration of aircraft and mission. A monitoring system tracks conditions and aircraft traffic in the airspace. Aircraft may be configured to transact with the management system including to obtain rights/priority by license and to operate in the airspace under direction of the system. The system and aircraft may be configured for dynamic transactions (e.g. licensing/routing). The system will set rates for licenses and use/access to the airspace and aircraft will be billed/pay for use/access of the airspace at rates using data from data sources. | 04-28-2016 |
20160117932 | Method and Apparatus For Locating A Target Using An Autonomous Unmanned Aerial Vehicle - Described herein is an unmanned aerial vehicle (UAV) system that incorporates sensor data to statistically minimize the time to autonomously locate a target on the ground. The system uses a two-stage approach to finding the RF target: 1) randomized flight, such as Lévy fight, to search the ground space and, 2) a geo-localization process, such as a simplex minimization process, to home in on the target. | 04-28-2016 |
20160117934 | AUTOMATED PACKAGE DELIVERY TO A DELIVERY RECEPTACLE - Improving automated package delivery to mobile delivery receptacles to allow accurate and reliable package deliveries comprises a delivery receptacle for an automated package delivery via an unmanned aerial delivery device. The delivery receptacle is notified of a pending delivery and travels to a receiving location. The delivery receptacle emits infrared (“IR”) beacons from one or more IR beacon transmitters. An aerial delivery device detects the IR beacon and uses the beacons to navigate to the delivery receptacle. The delivery receptacle receives IR beacon responses from the aerial delivery device and continually or periodically directs the IR beacons in the direction of the aerial delivery device. The aerial delivery device deposits the package in the delivery receptacle. After receiving the package, the delivery receptacle transports the package to a secure location, such as into a garage. | 04-28-2016 |
20160117935 | ELECTRIC TAXI MOTIVE CONTROL SYSTEM AND METHOD OF AN AIRCRAFT - An electric taxi motive control system of a first aircraft comprises a first aircraft position determining system configured to generate a first aircraft position signal, a first aircraft receiver, configured to receive transmissions of a second aircraft position signal, a first aircraft pilot interface configured to accept an input indicative of a first aircraft desired speed, and a first aircraft electronic controller configured to; determine a aircraft separation distance indicative of the distance between the first aircraft and the second aircraft, compare the aircraft separation distance with a safe distance value; and generate a modified first aircraft commanded speed signal when the aircraft separation distance is less than the safe distance value. | 04-28-2016 |
20160117936 | AUTONOMOUS VEHICLE AND METHOD FOR COORDINATING THE PATHS OF MULTIPLE AUTONOMOUS VEHICLES - A non-transitory processor-readable medium storing code causes a processor at a first vehicle (e.g., a first autonomous vehicle) to generate a first planned path based on a current position of the first vehicle and a mission requirement assigned to the first vehicle. A first planned path associated with a second vehicle (e.g., a second autonomous vehicle), which is based on a current position of the second vehicle and a mission requirement assigned to the second vehicle, is received at the first vehicle. After the first planned path associated with the second vehicle is received, a second planned path is generated based on the first planned path associated with the second vehicle and at least one of the mission requirement assigned to the first vehicle or the first planned path of the first vehicle. The second planned path of the first vehicle is transmitted to the second vehicle. | 04-28-2016 |
20160121998 | Method For Controlling An Aircraft Propeller System During Thrust Reversal - The present invention refers to a method for controlling an aircraft propeller system during thrust reversal, wherein it is checked whether each power plant is ready for the transition to negative pitch, and where the propellers transition to negative pitch is controlled from a flight control system, such as only when both power plants are ready for the transition to negative pitch, the flight control system instructs the aircraft propeller system to reverse thrust. If a power plant failure is detected before a reversal order is received, then the flight control system is informed of that failure condition, and then the flight control system will disable the thrust reversal operation as long as the failure condition remains. The method of the invention improves the aircraft controllability during landing operations, reduces pilot workload, and improves passenger comfort during landing and taxing. | 05-05-2016 |
20160122003 | FLY-BY-WIRE CONTROL SYSTEM FOR AIRCRAFT - The invention relates to a fly-by-wire system which comprises: three-stage piloting control, each stage including a control computer suitable for determining the positions of the stick, and a monitoring computer capable of verifying all the pre-determined positions of the stick; three-stage control-surface position calculation, each stage including a control computer suitable for calculating the control-surface positions from encoded positions of the stick, and a monitoring computer capable of verifying all the calculated control-surface positions; a single unidirectional communication link connecting the control computer of the first piloting control stage to the control computer of the first control-surface position calculation stage; a single unidirectional communication link connecting the control computer of the second piloting control stage to the control computer of the second control-surface position calculation stage; and a single unidirectional communication link connecting the control computer of the third piloting control stage to the control computer of the third control-surface position calculation stage. | 05-05-2016 |
20160122007 | Method for Defining and Controlling Aircraft Taxi Profile - A system and method are provided for defining, optimizing, and controlling taxi profiles for aircraft equipped with onboard non-engine drive means controllable to drive one or more nose or main landing gear wheels to drive an aircraft autonomously during taxi. An onboard taxi profile control system may employ smart software to determine selected taxi operational data at an airport and use this data to control and maintain torque of the drive means at desired selected levels that move the aircraft during taxi in response to determined taxi data or predetermined programmed taxi parameters. The system is designed to set default taxi profiles for each taxi cycle to achieve efficient aircraft taxi and to extend operational life of drive means components. Taxi profiles are modified and updated at periodic intervals or in real time in response to actual taxi conditions to optimize aircraft taxi at a specific airport. | 05-05-2016 |
20160122035 | SYSTEMS FOR AND METHODS OF PROVIDING INDICATORS USEFUL FOR PILOTING AN AIRCRAFT - The present disclosure provides a computer implemented method of providing an indicator useful for piloting an aircraft. The aircraft comprises an antenna configured to communicate with a transceiver. The method comprises: obtaining an antenna envelope characterizing directions relative to the aircraft for which a directive gain of the antenna exceeds a predetermined threshold; determining a direction of the transceiver relative to the aircraft; calculating a maneuvering range of the aircraft by comparing the antenna envelope and the transceiver direction, wherein the maneuvering range is indicative of eligible orientations of the aircraft for maintaining the transceiver within the antenna envelope; and outputting data indicative of the maneuvering range. | 05-05-2016 |
20160137307 | DEVICE FOR CONTROLLING A THRUST OF AT LEAST ONE AIRCRAFT ENGINE - A device for controlling a thrust of at least one aircraft engine. The device includes a display unit configured to display, on at least one display screen of the cockpit, indications regarding operation and at least the current engine speed of said engine of the aircraft, as well as a set of graphic elements including at least one graphic element, said graphic element or elements being configured to be able to be operated and activated by an operator to control at least one engine speed, said set of graphic elements including at least one graphic selection element configured to control the transition from the current engine speed to a preconfigured engine speed. | 05-19-2016 |
20160139597 | AIRCRAFT GROUND LIFT DUMP FLIGHT CONTROL FUNCTION - A flight control system for an aircraft includes at least one flight control computer that carries out a ground lift dump function that selectively extends a spoiler located on a wing of the aircraft into an airflow passing over the wing. The at least one flight control computer includes arming logic that is responsive to an input signal indicative of an aircraft parameter to automatically arm the ground lift dump function during certain phases of operation of the aircraft. The at least one flight control computer includes spoiler deployment logic that is responsive to an arming signal from the aiming logic which indicates that the ground lift function is armed to deploy the spoiler into its extended position within the airflow passing over the wing of the aircraft to assist in stopping the aircraft while the aircraft is on the ground. | 05-19-2016 |
20160139602 | LAUNCH-CONTROLLED UNMANNED AERIAL VEHICLES, AND ASSOCIATED SYSTEMS AND METHODS - Launch-controlled unmanned aerial vehicles, and associated systems and methods are disclosed. A computer-implemented method for operating an unmanned aerial vehicle in a representative embodiment includes detecting at least one parameter of a motion of the UAV as a user releases the UAV for flight. Based at least in part on the at least the one detected parameter, the method can further include establishing a flight path for the UAV, and directing the UAV to fly the flight path. | 05-19-2016 |
20160140851 | SYSTEMS AND METHODS FOR DRONE NAVIGATION - There is provided a method for navigation of a drone through a geographical air space, comprising: identifying a drone within or in proximity to a geographical air space; receiving flight data representing a certain flight path through the geographical air space; evaluating the flight data based on a flight risk map to determine the flight risk through the geographical air space, wherein the flight risk map includes zones, each zone being associated with a certain flight safety score; and one or more of: approving the certain flight path when the flight risk of the drone is within an acceptable risk threshold, blocking the certain flight path when the flight risk of the drone is outside the acceptable risk threshold, and obtaining external control of navigation of the drone to navigate the drone through at least one zone having the acceptable risk threshold. | 05-19-2016 |
20160144959 | Systems, Methods and Devices for Collecting Data at Remote Oil and Natural Gas Sites - Systems, methods and devices are provided for collecting operational data at remote oil and natural gas sites, such as wells, and or processing and refinery plants. One such system comprises a remote transmitter and/or controller at the site and an unmanned aerial vehicle (UAV), such as a drone aircraft, configured for aerial dispatch to the remote site and wireless connection to the remote transmitter for subsequent relay or upload of data to an external processor. The UAV may include still or video cameras for collecting images around the well site that can be uploaded and transmitted to the external processor. The system may also include logic-based applications allowing for feedback control of the well site to change operational parameters based on the received data. The system may also include a variety of sophisticated sensor devices on the UAV or located at the remote site to collect additional operational data, such as airborne particulate and/or toxic gas concentrations, audio files of pumps or other equipment and levels and properties of produced water and other fluids. | 05-26-2016 |
20160144971 | ASSISTING THE PILOTING OF A MULTI-ENGINED ROTORCRAFT IN AN ENGINE-FAILURE SITUATION, IN THE CONTEXT OF A MAIN ROTOR OF THE ROTORCRAFT BEING DRIVEN AT VARIABLE SPEED - A method of assisting the piloting of a multi-engined rotorcraft in the event of an engine failure. A main rotor of the rotorcraft is driven at a variable NR speed under the control of a control unit. Calculation means identify an authorized margin of mechanical power usable by the pilot depending on a rating for regulating the operation of each of the engines under the control of a regulator unit. Outside an engine-failure situation, and providing the main rotor is being driven at a low NR speed, the mechanical power margin that is usable by the pilot and that is displayed on a screen, is in fact a limited margin of a value less than the authorized margin. Under such conditions, and in an engine-failure situation, the mechanical power reserve that is actually available enables the pilot to counter rapidly the sudden drop in the NR speed of rotation of the main rotor as induced by the engine failure. | 05-26-2016 |
20160147224 | METHOD OF ERROR DETECTION OF AN AIRCRAFT FLIGHT MANAGEMENT AND GUIDANCE SYSTEM AND HIGH-INTEGRITY FLIGHT MANAGEMENT AND GUIDANCE SYSTEM - A method of error detection of a flight management system coupled with a guidance of an aircraft according to a flight plan, comprises the steps of: generating a first reference guidance order, monitoring the integrity of the first reference position, when the first reference position is not monitored as being dependable: invalidating the first FMS assembly and the associated guidance system, when the first reference position and the first reference trajectory are monitored as being dependable: generating a first monitoring guidance order, generating a first reference flight control, generating a first monitoring flight control, in monitoring the integrity of the first reference guidance order when the first reference guidance order is not monitored as being dependable: invalidating the first FMS assembly and the associated guidance. | 05-26-2016 |
20160147226 | AUTOMATED SERVICE MANAGEMENT - A computer-implemented method for automated service management includes identifying a period of time to perform a service on a transporter, wherein the transporter is one of: a vehicle, an aircraft, a watercraft, or a rail based transportation. A first location within a vicinity of the transporter is identified, wherein the vicinity is based at least in part on a known location of the transporter. The transporter is instructed to relocate to the first location and responsive to the computer determining the service of the transporter is complete, the transporter is instructed to relocate to the known location. | 05-26-2016 |
20160147236 | Engine Driven Pump (EDP) Automatic Depressurization System - An automatic engine driven pump (EDP) depressurization system for an aircraft is disclosed. The aircraft includes at least two EDPs driven by a main engine for converting mechanical power provided by the main engine into hydraulic power for distribution by a hydraulic system. The EDP depressurization system includes a depressurization device corresponding to each of the at least two EDPs and a control module. The depressurization devices are each energized to depressurize a respective EDP. The control module is in signal communication with each of the depressurization devices. The control module includes control logic for automatically generating a depressurization signal that energizes one of the depressurization devices based on a plurality of operational conditions of the aircraft. | 05-26-2016 |
20160152321 | VOLITANT VEHICLE ROTATING ABOUT AN AXIS AND METHOD FOR CONTROLLING THE SAME | 06-02-2016 |
20160154384 | Integrated Upsampler and Filtering for Multi-Rate Controller for Electromechanical Flight Actuation System | 06-02-2016 |
20160154391 | AVIONICS NETWORKS | 06-02-2016 |
20160159462 | SYSTEMS AND METHODS FOR CONFIGURABLE USER INTERFACES - A user interface presented to an operator of an unmanned aerial vehicle (UAV) may be presented to facilitate the ease of operation of the UAV. The information displayed in the user interface may be customized by the operator to display selected data. The display configuration data may be saved and imported into other systems for future use. Various entities related to one or more UAVs may be presented in a hierarchical tree structure illustrating the relationship between the entities. Electronic checklists may be presented to a user to facilitate addressing common and emergency situations. | 06-09-2016 |
20160161283 | SYSTEMS AND METHODS FOR DISPLAYING POSITION SENSITIVE DATALINK MESSAGES ON AVIONICS DISPLAYS - Systems and methods for displaying position sensitive datalink messages on avionics displays are provided. In one embodiment, a flight deck instrument display system for an aircraft comprises: a flight plan display screen that displays a graphical representation of at least a part of an aircraft's planned flight path together with symbology representing a position of the aircraft with respect to the aircraft's planned flight path; wherein the flight plan display screen further displays at least one symbol positioned along the graphical representation of at least a part of the aircraft's planned flight path that indicates a point of applicability for a received uplink datalink message. | 06-09-2016 |
20160163202 | MANAGING DATA EXCHANGE BETWEEN AN AVIONIC CORE AND AN OPEN WORLD DEVICE - A flight management system includes: an avionics core implementing generic aircraft management functionalities and providing services associated with the generic functionalities; at least one remote functionality in an open world part performing a function of interfacing between the avionics core and the open world applications run on the open world part which need to communicate with the avionics core, wherein the remote functionality ensures homogeneity and consistency of data exchanged and guaranteeing integrity and security of data exchanges, and an exchange interface of between the avionics core and the open world functionality supporting data exchanges. | 06-09-2016 |
20160163203 | FLIGHT CONTROL FOR FLIGHT-RESTRICTED REGIONS - Systems, methods, and devices are provided for providing flight response to flight-restricted regions. The location of an unmanned aerial vehicle (UAV) may be compared with a location of a flight-restricted region. If needed a flight-response measure may be taken by the UAV to prevent the UAV from flying in a no-fly zone. Different flight-response measures may be taken based on the distance between the UAV and the flight-restricted region and the rules of a jurisdiction within which the UAV falls. | 06-09-2016 |
20160163204 | TRANSPORTATION USING NETWORK OF UNMANNED AERIAL VEHICLES - Embodiments described herein include a delivery system having unmanned aerial delivery vehicles and a logistics network for control and monitoring. In certain embodiments, a ground station provides a location for interfacing between the delivery vehicles, packages carried by the vehicles and users. In certain embodiments, the delivery vehicles autonomously navigate from one ground station to another. In certain embodiments, the ground stations provide navigational aids that help the delivery vehicles locate the position of the ground station with increased accuracy. | 06-09-2016 |
20160163205 | VISIBILITY EVENT NAVIGATION METHOD AND SYSTEM - A method of visibility event navigation includes receiving, via processing circuitry of a client device, a first visibility event packet from a server, the first visibility event packet including information representing 3D surface elements of an environmental model that are occluded from a first viewcell and not occluded from a second viewcell, the first and second viewcells representing spatial regions of a specified navigational route within a real environment modeled by the environmental model. The method also includes acquiring, surface information representing the visible surfaces of the real environment at a sensor and determining, a position in the real environment by matching the surface information to the visibility event packet information. The method further includes transmitting, the position from the client device to the server and receiving a second visibility event packet from the server if the at least one position is within the specified navigational route. | 06-09-2016 |
20160169034 | CORE CASE HEATING FOR GAS TURBINE ENGINES | 06-16-2016 |
20160171896 | Commercial and General Aircraft Avoidance using Light Pattern Detection | 06-16-2016 |
20160171897 | FLIGHT MANAGEMENT SYSTEM AND METHOD FOR MONITORING FLIGHT GUIDANCE INSTRUCTIONS | 06-16-2016 |
20160171898 | COLLISION DETECTION SYSTEM | 06-16-2016 |
20160176504 | Wing Fold Controller | 06-23-2016 |
20160176510 | METHOD OF MANAGING DISCONTINUITIES IN VEHICLE CONTROL FOLLOWING A CONTROL TRANSITION, AND A VEHICLE | 06-23-2016 |
20160176512 | MULTI CORE VEHICLE MANAGEMENT SYSTEM AND METHODS | 06-23-2016 |
20160176535 | AIRCRAFT FUEL TANK INERTING ARRANGEMENT, METHOD OF INERTING ONE OR MORE AIRCRAFT FUEL TANKS, AIRCRAFT AND SOFTWARE PRODUCT | 06-23-2016 |
20160176541 | Aircraft Flight Control | 06-23-2016 |
20160179098 | RUDDER CONTROL METHOD AND SYSTEM FOR AN AIRCRAFT | 06-23-2016 |
20160180716 | METHOD AND SYSTEM FOR GUIDANCE OF AN AIRCRAFT | 06-23-2016 |
20160180717 | DYNAMIC SELECTION OF UNMANNED AERIAL VEHICLES | 06-23-2016 |
20160185446 | TRIM ADJUSTMENT DEVICE, AIRCRAFT, AND METHOD OF PERFORMING TRIM ADJUSTMENT - Trim adjustment devices | 06-30-2016 |
20160185447 | UNMANNED AERIAL VEHICLE ANGULAR REORIENTATION - A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value. | 06-30-2016 |
20160189548 | SUPERVISORY SAFETY SYSTEM FOR CONTROLLING AND LIMITING UNMANNED AERIAL SYSTEM (UAS) OPERATIONS - Systems, devices, and methods for determining, by a processor, an unmanned aerial system (UAS) position relative to at least one flight boundary; and effecting, by the processor, at least one flight limitation of a UAS if the determined UAS position crosses the at least one flight boundary. | 06-30-2016 |
20160189549 | SYSTEM AND METHOD FOR CONTROLLING AUTONOMOUS FLYING VEHICLE FLIGHT PATHS - A method is provided for limiting access to airspace by drones. The method includes receiving position information from a user associated with a property identified by the position information. The method also includes assembling the position information with other position information to compile a comprehensive configurable flight zone database. The method further includes pushing the configurable flight zone database to at least one drone. The drone accesses the configurable flight zone database to determine if movement is allowed, and the drone is programmed to not fly into areas identified in the configurable flight zone database. In the method, the drone may be further programmed to prohibit directing a camera into the areas identified in the configurable flight zone database. | 06-30-2016 |
20160189550 | SYSTEM AND METHOD FOR MANAGEMENT OF AIRSPACE FOR UNMANNED AIRCRAFT - A system and method for management of airspace for unmanned aircraft is disclosed. The system and method comprises administration of the airspace including designation of flyways and zones with reference to features in the region. The system and method comprises administration of aircraft including registration of aircraft and mission. A monitoring system tracks conditions and aircraft traffic in the airspace. Aircraft may be configured to transact with the management system including to obtain rights/priority by license and to operate in the airspace under direction of the system. The system and aircraft may be configured for dynamic transactions (e.g. licensing/routing). The system will set rates for licenses and use/access to the airspace and aircraft will be billed/pay for use/access of the airspace at rates using data from data sources. | 06-30-2016 |
20160195398 | HELICOPTER MOTION DETECTION DURING INERTIAL REFERENCE SYSTEM LEVELING | 07-07-2016 |
20160196756 | Piggybacking Unmanned Aerial Vehicle | 07-07-2016 |
20160200449 | SYSTEM AND METHOD FOR DAMAGE TRACKING AND MONITORING DURING GROUND HANDLING OF AIRCRAFT | 07-14-2016 |
20160200452 | WIRELESS ROTATING INSTRUMENTATION SYSTEM AND METHODS FOR DATA COLLECTION ON HELICOPTER ROTOR SYSTEMS | 07-14-2016 |
20160202168 | AIRCRAFT AND PARTICULATE DETECTION METHOD | 07-14-2016 |
20160202699 | CONTROLLED RANGE AND PAYLOAD FOR UNMANNED VEHICLES, AND ASSOCIATED SYSTEMS AND METHODS | 07-14-2016 |
20160202701 | ABNORMAL AIRCRAFT RESPONSE MONITOR | 07-14-2016 |
20160203723 | SYSTEM AND METHOD OF COLLISION AVOIDANCE IN UNMANNED AERIAL VEHICLES | 07-14-2016 |
20160252328 | Stationary and Mobile Test Device for Missiles | 09-01-2016 |
20160253907 | Systems and Methods for Restricting Drone Airspace Access | 09-01-2016 |
20160375984 | COUNTERBALANCING UNMANNED AERIAL VEHICLES DURING OPERATIONS ASSOCIATED WITH CELL TOWERS - Systems and methods using an Unmanned Aerial Vehicle (UAV) to perform physical functions on a cell tower at a cell site include flying the UAV at or near the cell site, wherein the UAV comprises one or more manipulable members; moving the one or more manipulable members when proximate to a location at the cell tower where the physical functions are performed to effectuate the physical functions; and utilizing one or more counterbalancing techniques during the moving ensuring a weight distribution of the UAV remains substantially the same. | 12-29-2016 |
20160375994 | METHOD OF ACTIVATING AN ELECTRIC MOTOR IN A HYBRID POWER PLANT OF A MULTI-ENGINED AIRCRAFT, AND AN AIRCRAFT - A method of driving rotation of a rotor of an aircraft, said aircraft having at least two fuel-burning engines and an electric motor suitable for driving rotation of said rotor. Said rotor is driven by using said engines together. An authorization is generated only during at least one predetermined stage of flight, said authorization authorizing the use of the electric motor in order to drive said rotor in rotation. While said authorization is valid and if one of said engines has failed, then an operation order is generated to require said electric motor to operate. While said operation order is valid, said rotor is driven by each engine that has not failed together with said electric motor. | 12-29-2016 |
20160376004 | UNMANNED AERIAL VEHICLE WITH DETACHABLE COMPUTING DEVICE - This disclosure is generally directed to an Unmanned Aerial Device (UAV) that uses a removable computing device for command and control. The UAV may include an airframe with rotors and an adjustable cradle to attach a computing device. The computing device, such as a smart phone, tablet, MP3 player, or the like, may provide the necessary avionics and computing equipment to control the UAV autonomously. For example, the adjustable cradle may be extended to fit a tablet or other large computing device, or retracted to fit a smart phone or other small computing device. Thus, the adjustable cradle may provide for the attachment and use of a plurality of different computing devices in conjunction with a single airframe. Additionally the UAV may comprise adjustable arms to assist in balancing the load of the different computing devices and/or additional equipment attached to the airframe. | 12-29-2016 |
20160378113 | DYNAMIC COMPLIANCE MONITORING OF UNMANNED VEHICLES - A system includes an unmanned vehicle (UV). A compliance unit receives sensor data from one or more sensors and compares the sensor data to a predetermined payload capacity threshold and a predetermined range capability threshold to determine compliance with a predetermined payload capacity and a predetermined range capability of the UV. The compliance unit generates a command to restrict the operation of the UV if the sensor data exceeds the predetermined payload capacity threshold and the predetermined range capability threshold of the UV. | 12-29-2016 |
20170233067 | INDEPENDENT CONTROL FOR UPPER AND LOWER ROTOR OF A ROTARY WING AIRCRAFT | 08-17-2017 |
20170233068 | LIFT OFFSET CONTROL OF A ROTARY WING AIRCRAFT | 08-17-2017 |
20170233088 | AIRCRAFT PARACHUTE DEPLOYMENT AUTOPILOT | 08-17-2017 |
20170233097 | UNMANNED AERIAL VEHICLE FLYING METHOD AND UNMANNED AERIAL VEHICLE FLYING SYSTEM | 08-17-2017 |
20170233099 | LIGHT EMISSION CONTROL APPARATUS, DRONE, AND METHOD FOR CONTROLLING EMISSION OF LIGHT | 08-17-2017 |
20170233105 | Visualization of Aggregated Maintenance Data for Aircraft Reliability Program | 08-17-2017 |
20170233112 | Polysynchronous Constellation Design | 08-17-2017 |
20170235316 | Airborne Relays in Cooperative-MIMO Systems | 08-17-2017 |
20180022446 | AIRCRAFT BRAKING SYSTEM HAVING A HIGH LEVEL OF AVAILABILITY | 01-25-2018 |
20180022454 | FLIGHT CONTROL METHOD AND APPARATUS | 01-25-2018 |
20180022456 | Mechanisms for Lowering a Payload to the Ground from a UAV | 01-25-2018 |
20180022472 | AUTONOMOUS SYSTEM FOR TAKING MOVING IMAGES FROM A DRONE, WITH TARGET TRACKING AND IMPROVED TARGET LOCATION | 01-25-2018 |
20180023974 | Flight Plan Preparing Method And Flying Vehicle Guiding System | 01-25-2018 |
20180024555 | UAV NAVIGATION AND SENSOR SYSTEM CONFIGURATION | 01-25-2018 |
20180025649 | UNMANNED AERIAL VEHICLE PRIVACY CONTROLS | 01-25-2018 |
20180025650 | Systems and Methods for Managing Drone Access | 01-25-2018 |
20180026706 | DEVICE FOR TRANSFERRING INFORMATION FROM AN AVIONICS SYSTEM OF AN AIRCRAFT TO AN INDEPENDENT COMPUTER | 01-25-2018 |
20190144102 | METHODS AND APPARATUS FOR CONTROLLING LANDING GEAR SHRINK | 05-16-2019 |
20190144116 | SYSTEMS AND METHODS FOR MULTI-ORIENTATION FLIGHT | 05-16-2019 |
20190144135 | METHOD FOR ESTIMATING THE PLAY IN AN ELECTROMECHANICAL ACTUATOR | 05-16-2019 |
20190145778 | UAV Flight Path Generating Method and Device | 05-16-2019 |
20190146490 | ENHANCED TAXI CONTROL FOR RIGID ROTORS | 05-16-2019 |
20190146501 | UNMANNED AERIAL VEHICLE LIGHT SHOW | 05-16-2019 |
20190147401 | SYSTEM AND METHOD FOR AUTOMATED PACKAGE DELIVERY TO DYNAMIC LOCATIONS | 05-16-2019 |
20190147749 | System and Method for Mission Planning, Flight Automation, and Capturing of High-Resolution Images by Unmanned Aircraft | 05-16-2019 |
20190147751 | UNMANNED AERIAL VEHICLE, DELIVERY SYSTEM, CONTROL METHOD FOR UNMANNED AERIAL VEHICLE, AND PROGRAM FOR CONTROLLING UNMANNED AERIAL VEHICLE | 05-16-2019 |
20190147756 | OBSTACLE AVOIDANCE SYSTEM | 05-16-2019 |
20220135210 | NONLINEAR FLY-BY-WIRE AIRCRAFT CONTROL - There is disclosed in one example a flight control computer for a rotary aircraft, including: a first interface to communicatively couple to a flight control input; a second interface to communicatively couple to flight geometry actuators; a data source; a multi-dimensional lookup table including a data structure to correlate flight control inputs to flight geometry actuator outputs according to a third-factor; and circuitry and logic instructions to: receive an input via the first interface; query the data source for the third-factor; query the multi-dimensional lookup table for a control input modifier according to the flight control input and the third-factor; and compute and send via a third interface a flight geometry output according to the control input modifier. | 05-05-2022 |
20220135218 | UNMANNED VEHICLE MAINTENANCE - An unmanned aerial vehicle includes a blade that is configured to rotate relative to a body of the unmanned aerial vehicle to enable the unmanned aerial vehicle to fly. The blade defines at least one cavity. The blade includes a power source and an auxiliary rotor configured to use the power source to rotate relative to the blade to cause the blade to fly. The auxiliary rotor is configured to withdraw into the at least one cavity. The blade is configured to decouple from the unmanned aerial vehicle. The auxiliary rotor is configured to extend from the at least one cavity and cause the blade to fly such that the blade navigates away from the unmanned aerial vehicle using the auxiliary rotor. | 05-05-2022 |
20220135245 | METHOD FOR RESILIENCY IN COMPUTE RESOURCES IN AVIONICS - A system and method for compiling and dynamically reconfiguring the management of functionalities carried among a set of multiple common compute nodes. During the inoperation of one node of the set of multiple common compute nodes, higher-criticality functionalities can be reassigned to other common nodes to ensure maintained operation of the higher-criticality functionalities. | 05-05-2022 |
20220137618 | INTELLIGENT MULTI-LEVEL SAFE AUTONOMOUS FLIGHT ECOSYSTEM - A communications ecosystem and related methods of operation include an ecosystem safety level (ESL), a plurality of vehicles or systems, each vehicle or system having an individual safety level (ISL), a control system operable to determine whether the ISL for each vehicle or system meets or exceeds the ESL, and one or more communications links between any first vehicle or system having a first ISL that does not meet or exceed the ESL and a second vehicle or system with a second ISL that does meet or exceed the ESL such that the first vehicle or system operates at the second ISL. | 05-05-2022 |
20220137646 | Anticipatory Dispatch of UAVs to Pre-staging Locations - An example method involves determining an expected demand level for a first type of a plurality of types of transport tasks for unmanned aerial vehicles (UAVs), the first type of transport tasks associated with a first payload type. Each of the UAVs is physically reconfigurable between at least a first and a second configuration corresponding to the first payload type and a second payload type, respectively. The method also involves determining based on the expected demand level for the first type of transport tasks, (i) a first number of UAVs having the first configuration and (ii) a second number of UAVs having the second configuration. The method further involves, at or near a time corresponding to the expected demand level, providing one or more UAVs to perform the transport tasks, including at least the first number of UAVs. | 05-05-2022 |
20220139233 | METHOD AND SYSTEM FOR UPDATING A FLIGHT PLAN - A method for updating, for an aircraft, a first flight plan having a first set of flight parameters, includes receiving, via an avionics device, a change to the first flight plan, determining a second set of flight parameters based on the change to the first flight plan, receiving, by the avionics device, at least one of terrain data and special use airspace (SUA) data. The method includes performing, with the avionics device, a safety validation of the second set of flight parameters, wherein the safety validation comprises: comparing the second set of flight parameters with the received at least one of terrain data and SUA data, and determining, based on the comparison, whether the second set of flight parameters presents a risk to safe flight. | 05-05-2022 |