| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 701008000 | Threshold or reference value | 61 |
| 20080300739 | METHOD OF GENERATING AN AIRCRAFT FLIGHT PLAN - The field of the invention is that of the generation of an aircraft flight plan. The invention more specifically relates to a method of generating a flight plan enabling an aircraft to link a departure airport AD to a destination airport AA. The flight plan consists of a number N−1 of segments SG | 12-04-2008 |
| 20090069959 | ALTITUDE RANGE FILTER FOR COCKPIT TRAFFIC DISPLAY - A system and method for filtering various targets (such as ground vehicles, stationary objects, and aircraft) from display on a display screen within the cockpit of an “Own Ship” aircraft. The system and method withhold from display any non-exempt targets that have an altitude that is either: (1) greater than an upper-threshold altitude; or (2) less than a lower-threshold altitude. The upper-threshold altitude and the lower-threshold altitude may be set to user-specified, customized values as desired to accommodate current flying conditions. In addition, the system and method may also be configured to operate in a plurality of operating modes, each of which features a different upper threshold altitude/lower threshold altitude combination. The system and method are preferably configured to reset certain threshold altitudes to pre-defined default altitudes in response to the aircraft landing. | 03-12-2009 |
| 20090099712 | PROCEDURE TO MINIMIZE THE RISK OF MID-AIR COLLISION FOR PERSONAL AIR VEHICLES - A method of and a system for controlling personal air vehicle (PAV) traffic provides a take-off-and-landing zone, and a forward flight zone. The take-off-and-landing zone may be from the ground up to a first altitude. The forward flight zone may be from the first altitude up to a second altitude. A maximum airspeed is provided in the take-off-and-landing zone. Minimum and maximum airspeeds are provided in the forward flight zone. In the forward flight zone there is a single heading for each altitude. Any change in heading must be accompanied by a change in altitude. | 04-16-2009 |
| 20090222151 | METHOD AND SYSTEM FOR LIMITING AN AIRCRAFT CONTROL SURFACE STEERING ANGLE - The disclosed embodiments concern a process for limiting the control surface steering angle of an aircraft, including operations to:
| 09-03-2009 |
| 20090292409 | RESPONDING TO AIRCRAFT EXCURSIONS FROM FLIGHT ENVELOPES - A method of monitoring an aircraft during use. Flight parameters of the aircraft are monitored to detect an excursion from a flight envelope. While the aircraft is still in flight, the monitored flight parameters are used to determine the severity of a detected excursion, aircraft component(s) possibly affected by the excursion are identified, and flight restrictions and/or inspections responsive to the excursion severity and identified component(s) are specified. This method provides valuable information to a flight crew about flight envelope excursions, can enhance passenger safety and can prevent unnecessary inspections and aircraft downtime. | 11-26-2009 |
| 20090292410 | PILOTING METHOD AND DEVICE AVOIDING THE PILOT INDUCED OSCILLATIONS - A piloting method and device avoiding the Pilot Induced Oscillations. | 11-26-2009 |
| 20100004801 | Air Navigation Aid Method and System Making it Possible to Maintain Vertical Margins - The invention relates to a calculation method for an aircraft navigation aid system making it possible to maintain a vertical safety margin with an obstruction profile, the aircraft comprising a navigation system, an automatic piloting system, a database system and a display device, characterized in that the method comprises the following steps: calculation of an obstruction altitude profile, calculation of a vertical safety margin with respect to the obstruction profile, of a plurality of vertical safety trajectories and of the respective flight setpoints for the aircraft to execute the trajectories, selection of the flight setpoints making it possible to maintain the aircraft as close as possible to the obstruction profile while maintaining between the aircraft and the obstruction profile at least the vertical safety margin, filtering of the flight set point values so that the variation of the values of the setpoints does not exceed a variation difference in a duration predefined in the system. | 01-07-2010 |
| 20100042272 | HYBRID ACARS COMMUNICATION SYSTEM - The invention concerns a communication system via ACARS messages intended to be placed onboard an aircraft, said system comprising a router ( | 02-18-2010 |
| 20100087970 | DYNAMIC ROLL ANGLE STALL PROTECTION FOR AN AIRCRAFT - A method, apparatus, and computer program product are present for operating an aircraft. A roll angle limit is identified using a load factor selected to allow a lateral maneuvering capability of the aircraft by forming an identified roll angle limit in response to vertical maneuvering of the aircraft. The vertical maneuvering of the aircraft is performed using the identified roll angle limit. | 04-08-2010 |
| 20100152931 | Meteorological Modelling Method for Calculating an Aircraft Flight Plan - The invention relates to a meteorological modelling method for calculating an aircraft flight plan, the aircraft comprising a communication means and a navigation management system. | 06-17-2010 |
| 20100250031 | PROPULSIVE GUIDANCE FOR ATMOSPHERIC SKIP ENTRY TRAJECTORIES - The invention set forth herein describes propulsive guidance methods and apparatus for controlling and shaping an atmospheric skip reentry trajectory for a space vehicle. Embodiments of the invention may utilize a powered explicit guidance algorithm to provide a closed-loop control method for controlling a space vehicle during a skip reentry maneuver. | 09-30-2010 |
| 20110196549 | Vertical Situation Awareness System for Aircraft - A method and apparatus for displaying a predicted path on a vertical profile to operate a vehicle. A path is predicted for the vehicle in response to an event occurring. The path has a turning section and a straight section after the turning section. A portion of terrain relative to the path predicted for the vehicle is identified. A vertical profile view of the terrain is displayed, including the portion of the terrain relative to the path predicted for the vehicle. | 08-11-2011 |
| 20110251740 | FOUR-DIMENSIONAL NAVIGATION OF AN AIRCRAFT - The present invention relates to methods of controlling the flight path of an aircraft to follow as closely as possible a predetermined four-dimensional flight path, such as when flying continuous descent approaches. A method of controlling an aircraft to follow a predetermined four-dimensional flight path is provided that comprises monitoring the actual along-track position and the actual vertical position of the aircraft relative to the corresponding desired positions on the predetermined flight path. The aircraft's elevators are used to correct deviations of the along-track position and the aircraft's throttle is used to correct deviations of the vertical position. | 10-13-2011 |
| 20120016539 | SYSTEMS AND METHODS OF ALTITUDE DETERMINATION - A system includes a memory device, and a processor coupled to the memory device. The processor is configured to receive, in a first time interval, from a first component a signal indicating an altitude of the aircraft, from a second component a signal indicating a first heading of the aircraft, and from a third component a signal indicating a first position of the aircraft. The processor is further configured to receive, in a second time interval later than the first time interval, and from the second and third components, signals respectively indicating a second heading and second position of the aircraft. The processor does not receive a signal from the first component in the second time interval. The processor is further configured to determine an estimated altitude of the aircraft and a geometric altitude of the aircraft. | 01-19-2012 |
| 20120016540 | Method And Device For Aiding The Control Of Guiding Modes Transitions Of An Aircraft - The device includes means ( | 01-19-2012 |
| 20120022724 | Automatic Management Method And Device Of A Lateral Trajectory For An Emergency Descent Of An Aircraft - Automatic management method and device of a lateral trajectory for an emergency descent of an aircraft. | 01-26-2012 |
| 20140200752 | Meteorological Modelling Method for Calculating an Aircraft Flight Plan - The invention relates to a meteorological modelling method for calculating an aircraft flight plan, the aircraft comprising a communication means and a navigation management system. | 07-17-2014 |
| 20140316616 | UNMANNED AERIAL VEHICLE AND METHODS FOR CONTROLLING SAME - One variation of a method for imaging an area of interest includes: within a user interface, receiving a selection for a set of interest points on a digital map of a physical area and receiving a selection for a resolution of a geospatial map; identifying a ground area corresponding to the set of interest points for imaging during a mission; generating a flight path over the ground area for execution by an unmanned aerial vehicle during the mission; setting an altitude for the unmanned aerial vehicle along the flight path based on the selection for the resolution of the geospatial map and an optical system arranged within the unmanned aerial vehicle; setting a geospatial accuracy requirement for the mission based on the selection for the mission type; and assembling a set of images captured by the unmanned aerial vehicle during the mission into the geospatial map. | 10-23-2014 |
| 20150378358 | METHOD FOR DETERMINING THE VERTICAL POINT FOR SWITCHING FROM A MANUAL PILOTING MODE TO A GUIDED MODE - A method for determining a switch-over vertical point from which an aircraft, having a current position, and flying a current vertical trajectory according to a manual piloting mode having an altitude setpoint, denoted target altitude, loaded by the pilot, switches to a piloting mode guided by a flight management system, in order to rejoin a predefined flight plan having a set of initial altitude constraints, comprising: calculating a first predicted vertical trajectory, determining a first point of intersection between the first predicted trajectory and the target altitude, determining a second predicted trajectory, determining the switch-over vertical point belonging to the first predicted vertical trajectory, based on any incompatible constraints, and as the intersection between the first predicted vertical trajectory and a predicted vertical trajectory calculated by integration of the dynamic flight equations by applying calculation hypotheses for a piloting mode guided by a flight management system. | 12-31-2015 |
| 20160011600 | Methods and Systems for Determining a Priority Sequence for Changing a Position or an Attitude of an Aircraft in Hover Flight | 01-14-2016 |
| 20160012730 | UNMANNED AERIAL VEHICLE COMMUNICATION, MONITORING, AND TRAFFIC MANAGEMENT | 01-14-2016 |
| 20160046373 | UNMANNED AERIAL VEHICLE AND METHODS FOR CONTROLLING SAME - One variation of a method for imaging an area of interest includes: within a user interface, receiving a selection for a set of interest points on a digital map of a physical area and receiving a selection for a resolution of a geospatial map; identifying a ground area corresponding to the set of interest points for imaging during a mission; generating a flight path over the ground area for execution by an unmanned aerial vehicle during the mission; setting an altitude for the unmanned aerial vehicle along the flight path based on the selection for the resolution of the geospatial map and an optical system arranged within the unmanned aerial vehicle; setting a geospatial accuracy requirement for the mission based on the selection for the mission type; and assembling a set of images captured by the unmanned aerial vehicle during the mission into the geospatial map. | 02-18-2016 |
| 20160046374 | UNMANNED AERIAL VEHICLE AND METHODS FOR CONTROLLING SAME - One variation of a method for imaging an area of interest includes: within a user interface, receiving a selection for a set of interest points on a digital map of a physical area and receiving a selection for a resolution of a geospatial map; identifying a ground area corresponding to the set of interest points for imaging during a mission; generating a flight path over the ground area for execution by an unmanned aerial vehicle during the mission; setting an altitude for the unmanned aerial vehicle along the flight path based on the selection for the resolution of the geospatial map and an optical system arranged within the unmanned aerial vehicle; setting a geospatial accuracy requirement for the mission based on the selection for the mission type; and assembling a set of images captured by the unmanned aerial vehicle during the mission into the geospatial map. | 02-18-2016 |
| 20160048131 | SYSTEM AND METHOD FOR DETERMINING A LENGTH OF AN EXTERNAL LOAD SLING - A system and method for determining length of load sling assembly in an aircraft, includes receiving, with a processor, information via one or more sensors regarding a load length during a delivery and descent state, the load length comprising length of a load sling assembly and a load height; controlling, with the processor, a minimum altitude of operation of the aircraft that ensures that the load does not touch the ground or obstacles during one or more of a flight plan, during decent, or during delivery; determining, with the processor, when a load has touched a ground in response to the receiving of the load length information; and releasing, with the processor, the load from the load sling assembly when the processor determines that the load has touched the ground. | 02-18-2016 |
| 20160062363 | SAFETY DEVICE AND SAFETY METHOD FOR AN AIRCRAFT, AND AIRCRAFT COMPRISING THE SAFETY DEVICE - For reducing a risk potential of an aircraft, a safety device for the aircraft is provided, said aircraft having a flight control device for flight control of the aircraft based on global position coordinates and/or flight altitude values of the aircraft detected by a sensor apparatus of the flight control device. The safety device comprises a flight altitude detection apparatus configured to detect a current flight altitude of the aircraft independently of the sensor apparatus, a determination apparatus configured to determine whether the current flight altitude of the aircraft detected by the flight altitude detection apparatus exceeds a predetermined maximum altitude, and a rescue apparatus configured to interrupt the flight control of the aircraft when the current flight altitude of the aircraft detected by the flight altitude detection apparatus exceeds the predetermined maximum altitude. | 03-03-2016 |
| 20160085238 | DISPLAY OF TERRAIN ALONG FLIGHT PATHS - Information about an air vehicle can be displayed, including a profile of terrain for a projected flight path of an aircraft. A first line at a first attitude above the profile of terrain can be displayed where the first line substantially follows the contour of the profile of terrain. A second line at a second attitude above the profile of terrain can be displayed where the second line substantially follows the contour of the profile of terrain. The display can also include an icon representing an altitude of the aircraft with respect to the profile of terrain. A third line projecting from the icon can be displayed to represent a command altitude for the projected flight path. | 03-24-2016 |
| 20160170416 | FLYING APPARATUS AND METHOD OF REMOTELY CONTROLLING A FLYING APPARATUS USING THE SAME | 06-16-2016 |
| 20160179096 | LAUNCHING UNMANNED AERIAL COPTER FROM MID-AIR | 06-23-2016 |
| 701009000 | Warning signal or alarm | 33 |
| 20080215197 | Method and Device for Detecting a Risk of Collison of an Aircraft with the Surrounding Terrain - The invention concerns a device ( | 09-04-2008 |
| 20080234882 | METHOD AND DEVICE TO ASSIST IN THE PILOTING OF AN AIRCRAFT IN A LANDING PHASE - Method and device to assist in the piloting of an aircraft in a landing phase. | 09-25-2008 |
| 20080243316 | Method For Setting an Aircraft Barometric Altitude - The invention relates to a method for aiding the setting of the barometric altitude of an aircraft equipped with a means ( | 10-02-2008 |
| 20080312780 | Methods, systems and computer program products for communicating auditory alert to aircraft - Systems, methods, and computer-program products for communicating auditory alerts about runway hazards to aircraft. A conflict on at least one arrival runway is identified using information received from an existing conflict detection system. An auditory alert associated with the conflict is generated and then modulated onto a carrier frequency. The carrier frequency may be a 75 MHz marker beacon carrier frequency, and further, the carrier frequency may be slightly offset from the 75 MHz marker beacon carrier frequency. The modulated alert is transmitted to an aircraft approaching the arrival runway through a directional antenna, which receives the transmitted auditory alert through a marker beacon receiver without requiring additional flight deck equipment. The transmitted alert does not interfere with transmissions from both an outer marker beacon associated with the arrival runway and marker beacons associated with adjacent runways due to transmitted power levels and antenna directivity. Also, with the transmitted carrier frequency shifted slightly from the marker beacon carrier frequency, the transmitted alert would not interfere with the inner or outer marker on the arrival runway. | 12-18-2008 |
| 20090005919 | Method and Device for Detecting a Lateral Dissymmetry of an Aircraft - Method and device for detecting a lateral dissymmetry of an aircraft. The detection device ( | 01-01-2009 |
| 20090012661 | DEVICE AND METHOD FOR CHANGING THE ZONES PROHIBITED TO AN AIRCRAFT - The present invention relates to a device and method for changing the zones prohibited to an aircraft. The method comprises a phase of defining the geometry of the restricted-access zones and their access conditions which depend on the aircraft, a phase of characterizing the aircraft with respect to the access conditions for the zones and a phase of determining the zones to which the aircraft has no access. | 01-08-2009 |
| 20090138145 | METHOD OF PROTECTING AN AIRCRAFT BY SIGNALLING AGAINST THE RISKS OF COLLISION WITH THE TERRAIN IN PROCEDURES WITH REDUCED PROTECTION CORRIDOR WITH SPECIFIC FUNCTIONS - The present invention relates to a method of protecting an aircraft in approach by signalling against the risks of collision with the terrain in steep-sided environments, in order to avoid unwanted warnings emanating from the clearance sensors of the onboard TAWS system while protecting the aircraft when it fails to observe the published procedure, and this equally in a landing procedure and in a take-off procedure. The method includes conferring an additional function on the conventional TAWS functions, specific to the detection of the potential risks of collision of the aircraft with the terrain when following procedures of reduced protection corridor type, and this without modifying either the logics or the characteristics of the clearance sensor or sensors as currently defined in the TAWSs of the state of the art. | 05-28-2009 |
| 20090157240 | ADVISORY SYSTEM TO AID PILOT RECOVERY FROM SPATIAL DISORIENTATION DURING AN EXCESSIVE ROLL - Systems and methods for outputting instructions when a vehicle is not responding to a roll-angle alert. An example system includes one or more altitude sensors that determine one of altitude above ground level or barometric altitude, one or more roll-angle sensors that determine the roll-angle of the vehicle, and a processor. The processor receives the altitude and roll-angle information, determines if an excessive roll-angle condition exists based on the received altitude and roll-angle information, and generates a roll-angle alert signal if a roll-angle alert condition exists. The processor generates a roll-direction signal based upon vehicle position relative to the horizon and outputs the determined roll-direction signal via the one or more output devices, if one of the condition still exists after the time delay, the vehicle roll-angle has deteriorated away from the desired threshold, or the roll-angle rate is greater than a roll-angle rate threshold. | 06-18-2009 |
| 20090157241 | METHOD OF PROTECTING AN AIRCRAFT BY SIGNALLING AGAINST THE RISKS OF COLLISION WITH THE TERRAIN IN PROCEDURES WITH REDUCED PROTECTION CORRIDOR - The present invention relates to a method of protecting an aircraft in approach by signalling against the risks of collision with the terrain in steep-sided environments, in order to avoid unwanted warnings emanating from the clearance sensors of the onboard TAWS system while protecting the aircraft when it fails to observe the published procedure, and this equally in a landing procedure and in a take-off procedure, and it is characterized in that it consists in modifying the characteristics of the clearance sensors according to the position deviation of the aircraft relative to the imposed RNP trajectory. | 06-18-2009 |
| 20090240386 | DEVICE FOR ISSUING AUTHORIZATION TO ACT ON THE OPERATING CONDITIONS OF AN AIRCRAFT ENGINE AND ENGINE CONTROL SYSTEM COMPRISING SAME - The invention concerns a device ( | 09-24-2009 |
| 20100010694 | SYSTEM FOR MONITORING RNP FOR SAFE TERRAIN CLEARANCE - Systems and methods for monitoring Required Navigational Performance (RNP) Procedures and reducing nuisance Enhanced Ground Proximity Warning System warnings including a processor, a memory with RNP instructions and data, and a communication device. The processor accesses the RNP data and instructions from the memory, and uses the communication device to obtain flight information from a Flight Management System of an aircraft. When the processor determines that the aircraft is in RNP space, the processor projects an RNP envelope and modifies a warning envelope of an EGPWS to coincide with the RNP envelope if the EGPWS warning envelope extends farther than the RNP envelope. | 01-14-2010 |
| 20100036550 | SYSTEMS AND METHODS FOR IMPROVING PILOT SITUATIONAL AWARENESS DURING LANDING - Systems and methods for generating an alert to the pilot of an aircraft during a deep/long landing situation. An example system includes a database that stores runway information, a position sensor that produces aircraft position information and a processor that is in data communication with the database and the position sensor. The processor includes an advisory condition detection component that compares altitude of the aircraft to a predefined altitude limit, determines if the aircraft is beyond an airline defined landing zone limit and not on the ground, and generates an alert to the pilot based upon the comparison and the determination. An output device outputs the generated alert. The airline defined landing zone limit is a fixed distance value from the approach end of a runway or a percentage of the total length of a runway, whichever allows for greatest amount of runway remaining. | 02-11-2010 |
| 20100042273 | METHOD AND DEVICE FOR AIRCRAFT, FOR AVOIDING COLLISION WITH THE TERRAIN - This system accompanies the alarms of TAWS type and in particular the alarms of “Avoid terrain” type indicating to the pilot that he has passed the limit point of success of a standard vertical avoidance maneuver, indications ( | 02-18-2010 |
| 20100082186 | METHODS AND SYSTEMS FOR INDICATING WHETHER AN AIRCRAFT IS BELOW A MINIMUM ALTITUDE CRITERION FOR A SECTOR - Methods and systems are provided for indicating whether an aircraft is below a designated minimum safe altitude level for an altitude sector. A method comprises displaying a graphical representation of a first sector on a display device associated with the aircraft. The first sector corresponds to a geographic area having a first minimum altitude criterion. If a current altitude of the aircraft is below the first minimum altitude criterion, the method continues by displaying the graphical representation of the first sector using a first visually distinguishing characteristic chosen to indicate that the aircraft is below the designated altitude level for the first sector. | 04-01-2010 |
| 20100094486 | Method and Device for Monitoring the Ability to Navigate of an Aircraft During a Phase of Flight Close to the Ground - The device ( | 04-15-2010 |
| 20100125381 | METHOD AND DEVICE OF TERRAIN AVOIDANCE FOR AN AIRCRAFT - According to the invention, a terrain avoidance maneuver is engaged when the alerts of a given pair of alerts are emitted simultaneously, the triggering of one of the alerts depending on the information provided by a first measurement chain and the triggering of the other alert of the pair relying on information provided by a second measurement chain, distinct from and independent of the first chain. | 05-20-2010 |
| 20100174424 | 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. | 07-08-2010 |
| 20100198432 | STABLE APPROACH MONITOR (SAM) SYSTEM - An improved stable approach monitor (SAM) system provides an audible advisory to a pilot when an aircraft is on a final landing approach. More specifically, the SAM system compares a measured airspeed of the aircraft to a predetermined flap placard speed. If the measured airspeed exceeds the predetermined flap placard speed then the improved SAM system provides an audible advisory indicating the airspeed of the aircraft is too fast. Advantageously, this audible advisory should prevent the pilot from attempting to deploy the flaps at an excessive airspeed and in turn focuses the pilot's attention on the problem at hand, which would be to reduce the airspeed of the aircraft. Once the airspeed is equal to or below the predetermined flap placard speed, the improved SAM system may provide another audible advisory informing the pilot to commence deployment of the flaps. | 08-05-2010 |
| 20100250032 | 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 comparing the current position of an aircraft, the planned path, and the constraint data. Current positions exceeding the tolerance cause the surveillance system to select the planned path as the future path to be followed. If initiation of a constraint has been detected and the current position is within the tolerance, the surveillance system selects the constrained path as the future path. | 09-30-2010 |
| 20100286851 | SYSTEMS AND METHODS FOR SELECTIVELY ALTERING A GROUND PROXIMITY MESSAGE - Systems and methods for selectively altering a ground proximity warning message. In an embodiment, a ground proximity warning system for a flight vehicle includes a processor that is configured to generate a look-ahead envelope that defines a region extending outwardly from the flight vehicle and to generate a terrain proximity message when the defined region intersects a terrain feature. An interface device is coupled to the processor that is operable to configure the system in a first operating mode wherein the generated terrain proximity message is selectively suppressed, and a second operating mode wherein the terrain proximity message is not suppressed. | 11-11-2010 |
| 20100292872 | METHOD AND DEVICE FOR AUTOMATICALLY DETECTING A LATERAL DISSYMETRY OF AN AIRCRAFT - The device ( | 11-18-2010 |
| 20100305784 | Embedded Ground Proximity Warning System for Helicopters - A system for warning a pilot of a helicopter of a flight-into-terrain hazard includes a signal processing component that determines helicopter flight conditions by fusing data obtained from multiple flight condition data sources, a protection component that communicates with the signal processing component, determines whether a potential controlled flight-into-terrain hazard exists by computing predicted recovery trajectories based upon flight conditions and characteristics of the helicopter and decides upon a recovery trajectory, and a pilot interface component that provides a directive to the pilot to indicate the decided-upon recovery trajectory if multiple predicted recovery trajectories indicate a terrain impact will occur. | 12-02-2010 |
| 20100305785 | METHOD AND DEVICE FOR ACTIVATING AN AUTOMATIC PILOTING MODE OF AN AIRCRAFT - A method and a device for activating an automatic piloting mode of an aircraft are disclosed. The device can include means for engaging an automatic pilot mode, when (i) the current distance of the aircraft with respect to a reference position on the ground belongs to a determined distance range, and (ii) the current height of the aircraft is at most equal to a reference height associated to the automatic pilot mode. | 12-02-2010 |
| 20110029162 | Systems and methods for selectively altering a ground proximity message - Systems and methods for selectively altering a ground proximity warning message. In an embodiment, a ground proximity warning system for a flight vehicle includes a processor that is configured to generate a look-ahead envelope that defines a region extending outwardly from the flight vehicle and to generate a terrain proximity message when the defined region intersects a terrain feature. An interface device is coupled to the processor that is operable to configure the system in a first operating mode wherein the generated terrain proximity message is selectively suppressed, and a second operating mode wherein the terrain proximity message is not suppressed. | 02-03-2011 |
| 20110035080 | Vertical Required Navigation Performance Containment with Radio Altitude - A monitor on-board an aircraft which uses radio altitude measurements as the basic observable altitude during runway approach. The basic concept utilizes the aircraft's navigation system, which includes means to store and retrieve radio altitude thresholds as a function of the distance along the desired path from the runway thresholds. These threshold functions are determined in advance based on a radio altitude reference which is defined as the expected radio altimeter measurement that would be made if the airplane were exactly on the desired reference path. Vertical containment monitoring is achieved by comparing the radio altitude measurement to computed thresholds for both too high and too low. During the approach, an annunciation message can be generated if the radio altitude measurement is above or below the threshold limits. Using this monitor ensures that the total system error for the aircraft is contained within a bound called the Vertical Containment Level of the desired reference path in space with a probability that is specified. | 02-10-2011 |
| 20110172855 | AIRCRACT ATTITUDE SYSTEMS AND RELATED METHODS - Aircraft attitude systems are provided. A representative aircraft attitude system includes: a detection system operative to determine an attitude of an aircraft in which the detection system is mounted; a warning system operative to alert a pilot when the attitude of the aircraft corresponds to at least one predefined attitude parameter from a set of predefined attitude parameters, the predefined attitude parameters including pitch, bank and yaw; and a recovery system operative to provide progressive flight control positioning directives to the pilot for returning the aircraft to a flight attitude within the predefined attitude parameters. | 07-14-2011 |
| 20110224849 | EMERGENCY DESCENT INTERVENTION SYSTEM - An emergency descent system for turbocharged piston engine powered aircraft. The flight management system is configured to challenge the pilot after a period of inactivity. Acknowledgment from the pilot resets the timer for subsequent challenge. Lack of timely pilot response sets off an alarm sequence. Lack of response to the alarm sequence sets off emergency descent by way of control by the flight management system of rate of descent, heading, ground track, and engine power by adjustment to the wastegate to the turbocharger. The control by the flight management system may incorporate direct control of the aircraft airspeed in the descent, and that may be enhanced by engine power adjustments. Upon reaching a selected target altitude, the aircraft engine power may be restored via the adjustment of the wastegate controller. At any time, when the pilot regains useful consciousness, the entire emergency descent sequence may be interrupted and normal control restored by the pilot. Additionally, the system may be configured to reset the aircraft transponder to an alarm code, in the event that the emergency descent sequence is initiated. | 09-15-2011 |
| 20110251741 | METHOD OF ALERT CALCULATION FOR AN AIRCRAFT GROUND PROXIMITY WARNING SYSTEM - The invention relates to a method of alert calculation for an aircraft obstruction proximity warning system including a step for detecting a hazardous flight situation capable of triggering an alert as a function of a data signal representing the change in height below the aircraft, including, prior to the step of detection, a step for converting the data signal representing the change in height as a function of information representative of the vertical profile of the obstructions below the aircraft. | 10-13-2011 |
| 20110276200 | SYSTEMS AND METHODS FOR PERFORMING EXCESSIVE NEGATIVE PITCH ALERT AND BIASING SINK RATE ALERT - Systems and methods that alert the pilot of the unusual negative pitch attitude. Additionally, the system can bias a “sink rate” envelope toward a more sensitive direction, such that the pilot can be alerted while (or before) a large sink rate is built up during an unusual negative pitch attitude condition. | 11-10-2011 |
| 20110276201 | TAWS WITH ALERT SUPPRESSION - An aircraft terrain awareness warning system is disclosed that includes an interface for entering flight plan details of an aircraft including at least one waypoint. The terrain awareness warning system is configured such that potential-terrain-collision alerts are suppressed in the aircraft during landing operations performed at waypoints associated with landing zones. | 11-10-2011 |
| 20120004792 | Weber-box, an aviation display device to support spatial awareness - A method for displaying information to a pilot or operator of a manned or unmanned aerial vehicle to facilitate safe operation of the aerial vehicle includes the steps of providing a display screen, displaying a three dimensional Cartesian coordinate system having a horizontal axis, a vertical axis and a depth axis on the display screen, displaying a model of an aerial vehicle on the screen in a manner that represents the position and velocity of the aerial vehicle relative to the coordinate system, displaying the horizontal axis and the vertical axis in a selected manner to indicate a potentially unsafe condition and providing an altitude display near the vertical axis. The display screen provides warnings to indicate unsafe conditions of altitude and pitch angle and includes objects that represent the ground. The ground objects move on the screen to indicate the speed and direction of the aerial vehicle. | 01-05-2012 |
| 20120004793 | AIRCRAFT HOVER SYSTEM AND METHOD - An aircraft hover system for enabling an aircraft to hover at a target spatial location represented by GPS location coordinates. The hover system includes a display screen rendering a display including live video feed of the terrain below the airborne aircraft, a first mark overlaying the video feed, the first mark representing the current position of the aircraft relative to the terrain, and a perimeter surrounding the first mark, the portion of the terrain within the perimeter being substantially magnified compared to that of the terrain outside of the perimeter. The hover system is configured such that, as the aircraft approaches the target spatial location, the distance between the first mark and a second mark on the display gradually decreases until and finally the first and second marks coincide; the second mark representing the target spatial location. | 01-05-2012 |
| 20140074324 | METHODS AND SYSTEMS FOR INDICATING WHETHER AN AIRCRAFT IS WITHIN DISTANCE AND ALTITUDE CRITERIA FOR AN IFR PROCEDURE TURN - Methods and systems are provided for displaying visually distinguishing characteristics if an aircraft is below a minimum altitude or beyond a maximum distance when executing a procedure turn. A procedure turn icon, an aircraft icon indicating the aircraft's present location, terrain/obstacles, and the visually distinguishing characteristics are displayed on a moving map. | 03-13-2014 |
