Class / Patent application number | Description | Number of patent applications / Date published |
701011000 | Auto pilot | 41 |
20080234883 | METHOD OF GENERATING INSTRUCTION VALUES FOR SERVO-CONTROLLING A FLIGHT PARAMETER P OF AN AIRCRAFT EQUIPPED WITH AN AUTOMATIC PILOT - The present invention relates to a method of generating instruction values for servo-controlling a flight parameter P of an aircraft equipped with an automatic pilot, between a current value C and a target value T. | 09-25-2008 |
20080243317 | System And Method For Controlling An Unarmed Air Vehicle - The invention relates to an unmanned air vehicle control system and method, designed such that, in one mission mode, the vehicle follows the mission route. The system comprises means ( | 10-02-2008 |
20080243318 | DEVICE AND METHOD FOR ASSISTING IN THE MANAGEMENT OF AN ENGINE FAILURE ON AN AIRCRAFT - A device and method for assisting in the management of an engine failure on an aircraft. | 10-02-2008 |
20080300740 | GPS autopilot system - The GPS (Global Positioning System) Autopilot System utilizes approximately fourteen (14) to twenty-four (24) microprocessors, depending on the size of the aircraft. These microprocessors computer control fuel and airspeed, ailerons, elevators, rudder and breaking automatically by following pre-programmed GPS fixes stored in the aircraft's onboard GPS database, and making the required mechanical system adjustments so that the real-time GPS fixes become the virtual GPS fixes when the aircraft moves. The GPS database is programmed during an identical flight plan, flown by an experienced pilot. During this flight, GPS coordinates and UTC time is recorded and stored in GPS database. All the stored GPS coordinates or fixes can be used or a portion of the flight fixes can be used, such as just the approach and landing sequence of GPS fixes. Once the chosen data is determined, the onboard database computer will control the aircraft's airspeed, yaw, pitch, roll and breaking to insure the aircraft passes through the GPS fixes that were recorded during the programming flight. The GPS Autopilot System accomplishes this by sighting the pre-programmed GPS fixes that are twelve (12) to thirty (30) seconds ahead of the aircraft's real-time GPS fix, and aiming or guiding the aircraft toward and through the programmed virtual GPS fixes. | 12-04-2008 |
20090082913 | METHOD AND APPARATUS FOR PREVENTING AN UNAUTHORIZED FLIGHT OF AN AIRCRAFT - A fly-by-wire (FBW) system ( | 03-26-2009 |
20090138146 | AUTOMATIC PILOT DEVICE AND METHOD WITH INSTINCTIVE TARGET LOCK-ON - The invention relates to automatic pilot devices on board aircraft, and more particularly aircraft of the maritime patrol or surveillance type. The invention is a device able to be engaged instinctively, calculating at least two flight path modes, the first one being a horizontal circular flight path around a location point and the second one being the overflying of a location point according to a heading chosen on a horizontal line, and making it possible to direct the aircraft automatically according to these two flight paths. | 05-28-2009 |
20090150013 | METHOD, SYSTEM, AND PROGRAM PRODUCT FOR AIRPORT TRAFFIC MANAGEMENT - Airport ground traffic management methods, program products and systems provided for a plurality of tags or tag readers distributed throughout an airport each spaced greater than a tag reader scanning distance. A traveling apparatus brings a tag proximate to a tag reader and a traffic manager in communication with the tag reader receives tag data and determines an apparatus location characteristic and formats the characteristic into a presentation provided to an apparatus operator or an airport ground traffic controller. Campus regions are identified in response to an airport campus function characteristic, and an apparatus location is plotted within a region on a graphic representation. In response to location, speed, historic data, data from other read tag and the location of another apparatus, a determined course of action is determined including entering a movement directive into an auto-pilot component. | 06-11-2009 |
20090150014 | COMPLEX AUTOMATED SYSTEM AND METHOD OF DISPLAYING AUTOMATION AIDS - A calculation system is disclosed having a pointing means. A display device presents the control interface of the system for the operator and the system triggering functions carries out a series of automation aids. The calculation system recovers the information descriptive of the automation aids programmed by the system while carrying out a function. The calculator system includes a means for displaying this information in a dialog area of the control interface of the function and has a direct access for the operator to the configuration of the parameters of the automation aids in the system. The invention applies to any complex automated system and finds a particularly beneficial application in respect of aircraft flight management systems. | 06-11-2009 |
20090177341 | METHOD OF DECOUPLING THE MODE OF AUTOMATIC FOLLOWING OF THE LATERAL PROFILE AND THE MODE OF AUTOMATIC FOLLOWING OF THE VERTICAL PROFILE - The present invention relates to a method of decoupling the mode of automatic following of the lateral profile and the mode of automatic following of the vertical profile of an automatic guidance system of an aircraft (A) flying on a reference trajectory (T). The mode of automatic following of the vertical profile is not disengaged immediately on disengaging the mode of automatic following of the lateral profile. After disengaging the mode of automatic following of the lateral profile, the mode of automatic following of the vertical profile is disengaged automatically only if at least one criterion of lateral separation between the current or short-term position of the aircraft and the lateral profile corresponding to the reference trajectory is satisfied, having regard to the position error. | 07-09-2009 |
20090177342 | METHOD OF APPLYING AN HTMB GUIDANCE DIRECTIVE - A method of applying a “Heading Then Merge Behind” (HTMB) guidance directive sent by an air traffic control center to an aircraft comprising a flight management system, the flight management system making it possible to automatically follow the trajectory of an active flight plan. The method includes reception and validation of the directive by the flight management system, confirmation by the pilot of the aircraft of the application of the directive, creation by the flight management system of a flight plan incorporating the directive, activation by the pilot of the flight plan incorporating the directive, so that the directive is executed automatically by the flight management system while following the trajectory of the flight plan incorporating the directive. | 07-09-2009 |
20100004802 | Navigating UAVS with an on-board digital camera - Methods, systems, and products are provided for navigating a UAV having an on-board digital camera. Embodiments include determining a desired digital resolution of an image of an object and piloting the UAV, under control of a navigation computer, in dependence upon the desired digital resolution of the image of the object. Determining a desired digital resolution of an image of an object may be carried out by identifying the object type, identifying the object size, and determining a required number of pixels for capturing the image of the object in dependence upon the object type and the object size. | 01-07-2010 |
20100076628 | APPARATUSES AND METHODS FOR DISPLAYING AUTOFLIGHT INFORMATION - Apparatuses and methods for displaying autoflight information and controlling autoflight systems. In one embodiment, a flight deck for an aircraft having an autoflight system includes at least one pilot seat, at least one window positioned forward of the pilot seat, and a forward instrument panel positioned forward of the pilot seat. In one aspect of this embodiment, the forward window provides a forward field of view out of the aircraft for a pilot seated in the pilot seat. In another aspect of this embodiment, the flight deck further includes a display device configured to provide information related to one or more autoflight modes. The display device can be positioned at least approximately between the forward instrument panel and the forward window to provide the pilot with autoflight information at least proximate to the forward field of view. In a further aspect of this embodiment, the display device can be configured to provide information related to one or more target flight parameters. | 03-25-2010 |
20100106348 | SWARM Autonomic Agents With Self-Destruct Capability - Systems, methods and apparatus are provided through which in some embodiments an autonomic entity manages a system by generating one or more stay alive signals based on the functioning status and operating state of the system. In some embodiments, an evolvable synthetic neural system is operably coupled to one or more evolvable synthetic neural systems in a hierarchy. The evolvable neural interface receives and generates heartbeat monitor signals and pulse monitor signals that are used to generate a stay alive signal that is used to manage the operations of the synthetic neural system. In another embodiment an asynchronous Alice signal (Autonomic license) requiring valid credentials of an anonymous autonomous agent is initiated. An unsatisfactory Alice exchange may lead to self-destruction of the anonymous autonomous agent for self-protection. | 04-29-2010 |
20100121503 | COLLISION AVOIDANCE SYSTEM AND A METHOD FOR DETERMINING AN ESCAPE MANOEUVRE TRAJECTORY FOR COLLISION AVOIDANCE - A collision avoidance system including a receiver configured to receive navigational data regarding intruding aerial vehicle and own aircraft. Storage is configured to store a plurality of predefined escape trajectories. A processor is configured to compare at least a subset of the predefined escape trajectories with a presumed trajectory of the intruding aerial vehicle and to select one of the predefined escape trajectories based on the comparison. The predefined escape trajectories are pre-simulated, wherein each escape trajectory is associated to a set of navigational data and to an escape manoeuvre direction. | 05-13-2010 |
20100168937 | Method for Flight Control of a Plurality of Aircraft Flying in Formation - In a method for the flight control of a plurality of aircraft flying in formation with respect to one another, correction signals are generated for an autopilot system or a command display in order to allow one or more following aircraft within the formation to follow a lead aircraft in the formation in a predeterminable relative position. A nominal trajectory of the following aircraft, parallel to the trajectory ( | 07-01-2010 |
20100174425 | METHOD AND DEVICE TO ASSIST IN THE DRIVING OF A VEHICLE, IN PARTICULAR OF AN AIRCRAFT, FOR THE AVOIDANCE OF OBSTACLES - A method and a device to assist in the driving of a vehicle, in particular of an aircraft, for the avoidance of obstacles. | 07-08-2010 |
20100174426 | AIRPLANE EMERGENCY NAVIGATIONAL SYSTEM - An emergency navigational system that monitors the navigation of an aircraft by comparing actual flight parameter data to predefined flight parameter data to thereby determine if the actual flight parameter data deviates beyond a defined value, and if so, activating a navigational controller to at least partially control the navigation of the aircraft. | 07-08-2010 |
20100250033 | Flight Management System Vector Functions - Disclosed is a system and method for diverting from a flight plan without adjusting an autopilot by treating a heading change as the new leg of a flight plan. The present invention allows the pilot of an aircraft to enter a heading to follow into a flight management system, which treats the heading as the current leg of a flight plan otherwise being followed by the flight management system. The present invention graphically displays the heading leg as the predicted track so that the pilot is able to see the airplane's expected path. Such a change allows the autopilot to continue following commands from the flight management system rather than being changed to a mode in which the autopilot follows heading commands directly from the pilot. | 09-30-2010 |
20100292873 | VEHICLE CONTROL SYSTEM INCLUDING RELATED METHODS AND COMPONENTS - An unmanned aerial vehicle variable autonomy control system is disclosed herein. In one embodiment, the system includes a control mode interface that provides a plurality of selectable control modes for an unmanned aerial vehicle, wherein one of the plurality of selectable control modes comprises a target tracking mode. Also included is a target editor interface provided in response to a selection of the target tracking mode, wherein the target editor interface facilitates receipt of an input indicative of a ground based moving target. The system also includes a communications component that transmits a command to the unmanned aerial vehicle, wherein the command is based at least in part on the input indicative of a target. | 11-18-2010 |
20100292874 | VEHICLE CONTROL SYSTEM INCLUDING RELATED METHODS AND COMPONENTS - An unmanned aerial vehicle variable autonomy control system is disclosed. In one embodiment, the system includes a control mode interface that provides a plurality of selectable control modes for an unmanned aerial vehicle, wherein one of the plurality of selectable control modes comprises an autonomous landing mode. Also included is a route editing interface that, following a selection of the autonomous landing mode, facilitates a receipt of an input indicative of a landing location. The system also includes a communications component that transmits a command to the unmanned aerial vehicle, wherein the command is based at least in part on the input indicative of the landing location. | 11-18-2010 |
20110022250 | Helicopter autopilot - The Helicopter Autopilot operates by recording GPS (Global Positioning System) and/or accellerometer coordinates on CD-ROM during a programming flight or maneuver. To autopilot this flight plan, the received GPS coordinates that show the pilot's real-time position, will be compared with the programmed GPS coordinates that represent the magnetic course high-lighted on the dashboard GPS terrain map display screen. The flight controls are computor adjusted until the helicopter is aligned with this pre-recorded magnetic course shown on the GPS display screen. The altitude, latitude, longitude and velocity are matched to these timed programmed coordinates. The automatic flight controls of the cyclic (main rotor tilt), the collective pitch (main rotor blades angle of attack), the anti-torque pedals (tail rotor blades angle of attack), and the throttle (engine power and RPM), which will change the yaw, pitch, roll and airspeed to again fly the helicopter through this pre-recorded GPS coordinate sequence. | 01-27-2011 |
20110125347 | APPARATUSES AND METHODS FOR DISPLAYING AUTOFLIGHT INFORMATION - Apparatuses and methods for displaying autoflight information and controlling autoflight systems. In one embodiment, a flight deck for an aircraft having an autoflight system includes at least one pilot seat, at least one window positioned forward of the pilot seat, and a forward instrument panel positioned forward of the pilot seat. In one aspect of this embodiment, the forward window provides a forward field of view out of the aircraft for a pilot seated in the pilot seat. In another aspect of this embodiment, the flight deck further includes a display device configured to provide information related to one or more autoflight modes. The display device can be positioned at least approximately between the forward instrument panel and the forward window to provide the pilot with autoflight information at least proximate to the forward field of view. In a further aspect of this embodiment, the display device can be configured to provide information related to one or more target flight parameters. | 05-26-2011 |
20110264309 | RANGE ESTIMATION DEVICE - A range estimation device for use in an aerial platform including at least one passive sensor, a trajectory determination unit and a control system. A control unit is arranged to indicate to the control system to perform own-ship maneuvering of the aerial platform such that characteristics of passive sensor measurements from the at least one passive sensor enable a range estimation to a target to be determined. The control unit is arranged to determine characteristics of the own-ship maneuvering based on the range uncertainty estimations to the target. A method and a computer program product for use in range estimation device. | 10-27-2011 |
20110276202 | SIMPLIFIED FLIGHT CONTROL SYSTEM INCLUDING A DECLUTCHABLE FRICTION DEVICE - The present invention relates to a friction device ( | 11-10-2011 |
20120029738 | AIRCRAFT CAPABLE OF HOVERING, AIRCRAFT MANEUVERING ASSIST METHOD, AND INTERFACE - An aircraft capable of hovering, and characterized by having at least one sensor, which has a plane sweep region and is designed to acquire, when the aircraft is manoeuvring, values of respective distances between first points on an obstacle within the plane sweep region, and a second point on the aircraft; and a control unit designed to generate an alarm signal when at least one of the first points lies within a safety region containing the second point on the aircraft. | 02-02-2012 |
20120059536 | System and method of automatic piloting for in-flight refuelling of aircraft, and aircraft comprising said system - An automatic-piloting system configured for being set on a receiver aircraft and for controlling operations of in-flight refuelling of said receiver aircraft, comprising: first detection means, set on the receiver aircraft and configured for acquiring first geometrical information associated to a first detection area and a second detection area belonging to a tanker aircraft, the first and second detection areas being linked together by a geometrical relation known to the automatic-piloting system; processing means, configured for determining, on the basis of the first geometrical information acquired, first position information associated to a relative position of the receiver aircraft with respect to the tanker aircraft; and an automatic-pilot device coupled to the processing means and configured for varying flight parameters of the receiver aircraft on the basis of the first position information. | 03-08-2012 |
20120277933 | Flight Controller Management System with a Backdrive Monitor - A method and apparatus for a monitoring module. The monitoring module is configured to identify a difference between measured position information for a controller and expected position information for the controller. The monitoring module is configured to compare the difference with thresholds for managing an autopilot in a control system of a vehicle to form a comparison. The monitoring module is configured to manage an operation of the autopilot based on the comparison such that the autopilot remains operating when a backdrive system is inoperative and an intentional override of the autopilot is absent. | 11-01-2012 |
20130013133 | SIMPLIFIED USER INTERFACE FOR AN AIRCRAFT - A user interface for an integrated autopilot and flight management system for an aircraft includes a plurality of tactical parameter controls for operation of the autopilot and a plurality of strategic parameter controls for operation of the flight management system. | 01-10-2013 |
20140163783 | METHOD FOR REGULATING THE TORQUE OF A CONTROL SURFACE ACTUATOR WITH A CONTROLLED ANGULAR POSITION ON AN AIRCRAFT WITH MECHANICAL FLIGHT CONTROL - A method for regulating an actuator for a control surface is provided, which actuator has an angular position controlled by an autopilot on an aircraft with mechanical flight control. When the value of the torque exerted by the actuator is less than a threshold torque value, the actuator is regulated in terms of position and the maximum speed of movement of the control surface is limited to a value that is dependent on the torque value. When the value of the torque exerted by the actuator is greater than the threshold torque value, the actuator is regulated in terms of torque. | 06-12-2014 |
20140244078 | MODULAR FLIGHT MANAGEMENT SYSTEM INCORPORATING AN AUTOPILOT - A modular vehicle management system is described, comprising a controller module configured to control different types of carrier modules. The controller module includes a computer system and optionally one or more sensors. The computer system is configured to perform operations comprising detecting whether a carrier module is connected to the controller module. If the carrier module is connected to the controller module, the carrier module is authenticated. If the authentication fails, operation of the vehicle is inhibited. The control module is configured to determine carrier module capabilities including information regarding a navigation processing device, and/or a radio modem. The controller adapts to the capabilities of the controller module. Using information from the sensors and the navigation processing device, the vehicle management system navigates the vehicle. | 08-28-2014 |
20140288732 | Automatic Piloting Method And System For An Aircraft - The automatic piloting system includes an element for automatically supplying a computation unit, when the aircraft is guided according to a descending corrected speed and a new corrected speed which is greater than the corrected speed used for guidance of the aircraft is input by the pilot, with a predetermined maximum Mach number which replaces the current Mach number and which is intended to form, together with the new input corrected speed, a pair of speeds which is taken into account by the computation unit for determining the guidance instructions for the aircraft. | 09-25-2014 |
20140330458 | METHOD AND SYSTEM FOR DETERMINING AN AIRSPEED OF AN AIRCRAFT - A method and system for determining an airspeed of an aircraft, known as assisted aircraft, comprises: a) determining a position; b) measuring a ground speed; c) receiving a plurality of messages from a plurality of other assisting, aircraft, each message containing a first item of information, indicating a position of an assisting aircraft, and a second item of information, indicating a wind speed at the position; d) estimating a wind speed at the position of the assisted aircraft by interpolating the wind speed values at the positions of the assisting aircraft obtained in step c); and e) computing a true speed of the assisted aircraft by using the vector difference between its ground speed, measured in step b), and the wind speed estimated in step d). The method can check operation of an anemometric subsystem aboard an aircraft, to compensate for any malfunction and/or to enable automatic piloting. | 11-06-2014 |
20150309513 | AUTOMATIC FLIGHT CONTROL METHOD FOR A ROTORCRAFT ENABLING THE ROTORCRAFT TO MAINTAIN A PATH BY TRACKING MANUAL FLIGHT CONTROLS - A method of enabling an autopilot ( | 10-29-2015 |
20150339929 | 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. | 11-26-2015 |
20150367956 | AIRCRAFT LANDING MONITOR - According to an aspect, a method of monitoring landing of an aircraft includes determining whether the aircraft is in a landing phase to maneuver the aircraft to a landing zone. Either or both of a landing profile monitor and a pattern matcher can set a landing instability indicator. The landing profile monitor compares aircraft sensor data indicative of a current state of the aircraft to a landing profile of the aircraft and sets the landing instability indicator based on the landing profile. The pattern matcher identifies a pattern associated with the landing zone in perception sensor data indicative of current conditions at the landing zone, monitors the pattern for a change indicative of landing zone instability, and sets the landing instability indicator based on detecting the change indicative of landing zone instability. Landing abort logic is triggered to abort landing based on determining that the landing instability indicator is set. | 12-24-2015 |
20160068267 | CONTEXT-BASED FLIGHT MODE SELECTION - Systems and methods for controlling an unmanned aerial vehicle within an environment are provided. In one aspect, a system comprises one or more sensors carried by the unmanned aerial vehicle and configured to provide sensor data and one or more processors. The one or more processors can be individually or collectively configured to: determine, based on the sensor data, an environment type for the environment; select a flight mode from a plurality of different flight modes based on the environment type, wherein each of the plurality of different flight mode is associated with a different set of operating rules for the unmanned aerial vehicle; and cause the unmanned aerial vehicle to operate within the environment while conforming to the set of operating rules of the selected flight mode. | 03-10-2016 |
20160125746 | DYNAMIC COLLISION-AVOIDANCE SYSTEM AND METHOD - An obstacle-avoidance system for a vehicle, the obstacle-avoidance system may comprise: a communication device; a plurality of sensors, the plurality of sensors configured to detect collision threats within a predetermined distance of the vehicle; and a processor. The processor may communicatively couple to the communication device and the plurality of sensors and configured to receive navigation commands being communicated to a control system via said communication device. The processor may also receive, from at least one of said plurality of sensors, obstruction data reflecting the position of an obstruction. Using the obstruction data, the processor identifies a direction for avoiding said obstruction. In response, the processor may output, via said communication device, a command to said control system causing the vehicle to travel in said flight direction. | 05-05-2016 |
20160152323 | AIRCRAFT, SYSTEMS, AND METHODS FOR TRIM CONTROL IN FLY-BY-WIRE AIRCRAFT SYSTEMS | 06-02-2016 |
701012000 | Inner/outer loop | 3 |
20110077803 | METHOD AND DEVICE FOR DETECTING PILOTING CONFLICTS BETWEEN THE CREW AND THE AUTOPILOT OF AN AIRCRAFT - According to the invention, the method comprises checking (in | 03-31-2011 |
20110184593 | System for facilitating control of an aircraft - A system for providing flight control instructions to an aircraft is claimed, wherein using aircraft position or velocity data, an outer control loop algorithm determines an aircraft target angle and an inner control loop algorithm outputs commands to cause the aircraft to achieve the target angle. Utilizing the commands outputted from the control loops, aircraft are able to autonomously take-off and land, station hold in a very precise manner, and fly in very close proximity to other objects with little chance of collision. | 07-28-2011 |
20140365042 | Method and System for Aircraft Speed Control - The invention relates to methods and systems for controlling the speed of an aircraft. The methods and systems disclosed herein are particularly advantageous for unmanned aerial vehicles. A system may include an outer-loop controller, wherein the outer-loop controller is arranged to receive one or more target flight variables and to output a nominal target pitch; an inner-loop controller arranged to receive a target pitch and output a control signal for controlling at least one aircraft control device; and a saturation module arranged to receive a nominal target pitch and to output a target pitch for the inner-loop controller, wherein the nominal target pitch is limited between an upper bound and a lower bound by the saturation module to generate the target pitch. | 12-11-2014 |