Abstract: 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.

Abstract: A method of determining lubrication oil consumption in a gas turbine engine that has an engine operating cycle interval comprising a starting phase, a running phase and a shutdown phase, comprises the steps of: measuring lubrication oil level upon initialization of the starting phase of each engine operating cycle interval; comparing the starting phase measured lubrication oil level during the starting phase with a starting phase baseline lubrication measurement; recording the starting phase lubrication oil level measurement; determining average engine lubrication oil consumption rate during the complete engine operating cycle interval by dividing the difference between the starting phase lubrication oil measurement and the baseline lubrication oil measurement; and repeating these steps for each subsequent engine operating cycle interval; wherein the starting phase baseline lubrication oil level measurement is initially a predetermined lubrication oil level and then the previous starting phase lubrication oil

Abstract: Method and device for ensuring the safety of a low-altitude flight of an aircraft. The device (1) comprises a recording means (8) corresponding to an operation critical instrument for recording, during a low-altitude flight, one part at least of the lateral trajectory of the flight trajectory situated ahead of the current position of the aircraft, a monitoring means (11) for monitoring, during a low-altitude flight, the availability at least of said lateral trajectory, and a guidance system (3) for taking the aircraft up to a safe altitude, taking into account said part of the trajectory recorded by said recording means (8), when said monitoring means (11) has detected a loss of said lateral trajectory.

Abstract: 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.

Abstract: 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.

Abstract: A portable communication device detects a current speed of travel of the portable communication device independent of any vehicle temporarily transporting the portable communication device. A speed based setting controller of the portable communication device compares the current speed to at least one threshold value set at the portable communication device. Responsive to the current speed exceeding the threshold value, the speed based setting controller automatically assigns a separate speed based setting to a current setting for each feature assigned to the threshold value, wherein each current setting for each feature designates the operability of that feature within the portable communication device, such that the current setting for each feature adjusts with a speed of travel as detected by the portable communication device.

Abstract: A driver assistance system for a vehicle includes an imaging device having a field of view forward of a vehicle and in a direction of travel of the equipped vehicle, an image processor operable to process image data captured by the imaging device, and a global positioning system operable to determine a geographical location of the vehicle. The equipped vehicle includes an adaptive speed control system for controlling the speed of the equipped vehicle. The adaptive speed control system may reduce the speed of the equipped vehicle responsive at least in part to a detection of a curve in the road ahead of the equipped vehicle via processing by the image processor of image data captured by the imaging device.

Abstract: Method and device for constructing a low altitude flight trajectory intended to be followed by an aircraft. The device (1) comprises, in particular, a means (6) for constructing a lateral trajectory of the flight trajectory and a means (7) for constructing a vertical trajectory of the flight trajectory, over a profile section defined between two height maxima of a terrain profile, by displacing over the terrain profile a V-shaped construction profile, whose branches are determined respectively by maximum angles of climb and of descent and by selecting a position of the construction profile, for which its edges arrive tangential to the terrain profile, and no peak of the terrain profile crosses the construction profile, the position thus selected of the construction profile allowing the latter to form the part of the vertical trajectory which is situated at the level of said profile section.

Abstract: 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.

Abstract: A method is provided for indicating the boundaries of a required navigational performance (RNP) corridor on an aircraft's map display. The method includes the steps of producing an aircraft leg segment symbol on the map display, establishing an RNP value, and scaling the RNP value to the map display field of view. The method further includes the step of generating an RNP corridor boundary graphic on the map display offset from the aircraft leg segment symbol by the scaled RNP value.

Abstract: Methods and systems are provided for using a measurement of only one axis of a three-axis magnetometer to perform at least one corrective action on an unmanned aerial vehicle (“UAV”). An exemplary embodiment comprises (i) receiving from a three-axis magnetometer a measurement representative of an attitude of a UAV, wherein the measurement is of only one axis of the magnetometer, (ii) comparing the measurement to an allowable range of attitudes, (iii) determining that the measurement is not within the allowable range of attitudes, and (iv) performing at least one corrective action on the UAV.

Abstract: 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.

Abstract: A driver assistance system for a vehicle includes an imaging device having a field of view forward of a vehicle equipped with the driver assistance system and in a direction of travel of the equipped vehicle. The imaging device is operable to capture image data and an image processor is operable to process image data captured by the imaging device. The equipped vehicle includes an adaptive speed control system for controlling the speed of the equipped vehicle, and the speed of the equipped vehicle is controlled by the adaptive speed control system at least in part responsive to processing by the image processor of image data captured by the imaging device.

Abstract: Navigation of an aircraft is facilitated through the displaying on a map of an over flown region, and of the limits of zones within range of the aircraft in an emergency situation. The points of the zones within range of the aircraft are tagged on the basis of: an estimate of the vertical margins to reach these points, taking into account non-maneuverability zones neighboring the aircraft to be circumvented; a vertical flight profile to be complied with; and a safety height margin.

Abstract: One popular military aircraft mission is to meet or rendezvous with another aircraft. Presently used systems have limitations in rendezvous distance, low accuracy of computed rendezvous intercept position, and wrong results in special rendezvous scenarios such in polar regions or on a collision path. The present invention makes use of a numerical algorithm to accurately compute the rendezvous interception position with a preselected tolerance/resolution. The algorithm makes no assumption of angles and uses a proven Sodanos equation to compute a distance between two points on the earth or to compute a second position away from a first position at a known distance and bearing. Using the invention, the rendezvous intercept position can be computed with greater accuracy and a further distance in any region of the globe than the prior art methods and can be used even if the aircraft are in a rendezvous or collision/chasing path.

Abstract: The invention relates to a method and a device for constructing a low-altitude flight path to be followed by an aircraft. The device comprises a database including a terrain profile concerning the terrain to be flown over by the aircraft, a set of data sources, first unit for determining a lateral trajectory of the flight path, and second unit for determining a vertical trajectory of the flight path, the second unit being formed so as to determine the vertical trajectory during the aircraft flight, successively as the flight proceeds, segment by segment, and including an element for retrieving from the database a profile section, and an element for determining a vertical trajectory segment, using the retrieved profile section, based on the climb-out and let-down performances of the aircraft derived from the set of data sources.

Abstract: System, method and computer program product for determining bearing using ADS-B and TCAS standard reply bearing estimates are disclosed. In one embodiment, a method for determining bearing based upon ADS-B signals includes receiving ADS-B signals and standard transponder reply signals. A first bearing estimate is based on the ADS-B signal. A second bearing estimate is based on the standard transponder reply signals. A database is developed according to the first and second bearing estimates via the ADS-B and standard transponder reply signals. In one embodiment, where ADS-B signals are unavailable, associated ADS-B signals associated with the standard transponder reply previously stored in the database are used to determine bearing.

Abstract: Method and device for ensuring the safety of a low-altitude flight of an aircraft. A device (1) for ensuring the safety of a low-altitude flight comprises information sources (5) able to determine current flight conditions, a monitoring unit (6) for realizing, with the aid of said current flight conditions, a function for global and autonomous monitoring of said low-altitude flight of the aircraft, making it possible to preserve the integrity of said aircraft during said flight, and means (13) for presenting the results of the monitoring function realized by said monitoring unit (6) to an operator.

Abstract: 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.

Abstract: A method of transitioning from a complex response flight state to a ground operation control state. Pilot intent is determined through collective position information to control the transition. An independent cockpit switch activates an emergency surface contact transition function for use with a fly-by-wire (FBW) flight control system. Once the surface contact transition function is active, FBW control laws transition from a fully augmented flight state, through an augmentation deactivation state and into the surface contact state.

Abstract: 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. The method comprises at least the following steps: the communication means carries out the acquisition of meteorological prediction data related to waypoints in proximity to the nominal route in addition to the waypoints belonging to the nominal route, the navigation management system allocates by projection onto the current route of the aircraft the prediction data for the said waypoints not belonging to the current route, the navigation management system calculates the meteorological prediction data for the waypoints of the current route of the flight plan according to the prediction data allocated by projection onto the current route of the aircraft. The invention is a modelling method for aircraft navigation management systems.

Abstract: A method for automatically monitoring and alerting a fuel leak downstream of an engine fuel flow meter in an aircraft is provided. The method uses existing engine sensor data to input into a predetermined parameter model to predict the nominal fuel flow, and also compares fuel flow between a left engine and a right engine.

Abstract: The invention relates to a method for controlling an internal combustion engine with a motor control system that adjusts the exhaust-gas temperature by influencing the air-fuel mixture. Said motor control system has a temperature model so as to determine a preset temperature for a component in the exhaust manifold, which is achieved after a longer period of time while maintaining current operating and driving conditions. The motor control system regulates the exhaust-gas temperature depending on the preset temperature for the purpose of component protection.

Abstract: A system includes an angular rate sensor disposed in a vehicle for providing angular rates of the vehicle, and an instrument disposed in the vehicle for providing line-of-sight control with respect to a line-of-sight reference. The instrument includes an integrator which is configured to integrate the angular rates of the vehicle to form non-compensated attitudes. Also included is a compensator coupled across the integrator, in a feed-forward loop, for receiving the angular rates of the vehicle and outputting compensated angular rates of the vehicle. A summer combines the non-compensated attitudes and the compensated angular rates of the to vehicle to form estimated vehicle attitudes for controlling the instrument with respect to the line-of-sight reference. The compensator is configured to provide error compensation to the instrument free-of any feedback loop that uses an error signal. The compensator may include a transfer function providing a fixed gain to the received angular rates of the vehicle.

Abstract: A device to assist in an independent piloting of an aircraft at least in a descent phase includes a unit to determine a descent axis which assists a pilot in flying from a safe altitude to a decision height, the descent axis being secured relative to the ground being flown over, and a guidance system to assist in the guiding of the aircraft along said descent axis in a descent phase.

Abstract: Method and system for evaluating and implementing air traffic management tools and approaches for managing and avoiding an air traffic incident before the incident occurs. The invention provides flight plan routing and direct routing or wind optimal routing, using great circle navigation and spherical Earth geometry. The invention provides for aircraft dynamics effects, such as wind effects at each altitude, altitude changes, airspeed changes and aircraft turns to provide predictions of aircraft trajectory (and, optionally, aircraft fuel use). A second system provides several aviation applications using the first system. These applications include conflict detection and resolution, miles-in trail or minutes-in-trail aircraft separation, flight arrival management, flight re-routing, weather prediction and analysis and interpolation of weather variables based upon sparse measurements.

Abstract: The present invention relates to an aircraft with wings whose maximum lift can be altered by controllable wing components. By means of a regulating device, depending on flight state parameters and the actually measured load on the wings, wing components are acted upon such that, as a precautionary measure, the maximum possible aerodynamic lift does not exceed a desired upper limit value.

Abstract: 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.

Abstract: In distance maps used in order to facilitate the navigation of craft such as an aircraft, the distances estimated take into account obstacles to be circumvented but not the maneuverability of the craft. The adaptation route required by the craft in order to take the right direction is not taken into account so that certain distance estimates for accessible points located in the neighborhood of the craft are unrealistic. In order to make a distance map more realistic, it is proposed that an obstacle of concave shape associated with the craft be added behind the position of the craft, forcing the estimations of distances to be circumvented an area that is inaccessible to the craft for reasons of maneuverability.

Abstract: 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.

Abstract: Embodiments of the invention include a system for displaying an audit diagram. The system includes a monitor capable of electronically displaying the audit diagram. The monitor includes a text equivalent constructed from an input text, and a conversion representation including an operator indicator, a result arrow, and a rule arrow.

Abstract: 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.

Abstract: Methods and systems are provided which warn a pilot or flight crew to prevent navigation of an aircraft into an unapproved region of operation. A boundary of an approved region of operation for the aircraft is identified. A position of the aircraft relative to the boundary of the approved region of operation is determined. Then, a warning is generated if the determined position of the aircraft relative to the boundary of the approved region of operation satisfies a predetermined criteria.

Abstract: The invention concerns a communication system via ACARS messages intended to be placed onboard an aircraft, said system comprising a router (310, 310?) adapted to route said messages from and to a plurality of VHF, HF, SATCOM sub-networks. The system comprises a switch (360, 365) and an AoIP conversion gateway (380), the switch being connected to an HF or SATCOM transceiver module (340, 350) by means of a first two-way link (341, 351), and to said AoIP gateway by means of a second two-way link (381), the switch being adapted to select said first two-way link when it lies in a first switch position and the second two-way link when it lies in a second switch position, the switch lying in the second switch position if the aircraft is on the ground or less than a predetermined distance from the ground, otherwise it lies in the first position.

Abstract: 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.

Abstract: Multiple data and images are multiplexed and sequenced in order to minimize the recording and monitoring hardware required to process the images, providing a detailed record of an event, greatly enhancing event reconstruction efforts. The multi-media safety and surveillance system for aircraft incorporates a plurality of strategically spaced sensors including video imaging generators for monitoring critical components and critical areas of both the interior and the exterior of the aircraft. The captured data and images are recorded and may be transmitted to ground control stations for real time or near real time surveillance. The system includes a plurality of strategically located video image sensors such as, by way of example, analog and/or digital video cameras, a video data recorder (VDR) and a pilot display module (MCDU or MIDU). All data is in recorded in an IP format. The IP encoder may be an integral component of the VDR, or the data may be transmitted in an IP format from the data generator device.

Abstract: The air-to-ground cellular network for deck-to-deck call coverage provides call coverage to customers who are located in aircraft that are flying within the arrival/departure airspace of an airport by trifurcating the spatial coverage regions or volumes of space to solve the problems of inter-network interference while yielding air-to-ground cellular network coverage at any altitude. Three types of cells are considered: an Outer Cell, an Inner Cell and an Airport Cell. The Outer Cell is a macro cell covering a large volume of space and is one of many cells in the composite air-to-ground cellular network. The Inner Cell is created within an Outer Cell and has at its center an airport. The Airport Cell is a part of the Terrestrial Cellular Network (TCN), created by the present terrestrial cellular operators or service providers.

Abstract: This method uses for the estimation of a distance, a propagation distance transform considering only the paths which are both accessible to the aircraft taking account of its vertical flight profile and complying with air regulations. The propagated distance Dp is accompanied by a propagated altitude Ap which at all points follows the vertical flight profile of the aircraft, while being greater than the altitudes of these points and complying with the air regulation constraints at these points. This is obtained by subjecting the propagation to compliance with the vertical flight profile of the aircraft, constraints of the elevations of the points of the relief and air regulation constraints.

Abstract: A terrain awareness and warning system includes electronics for receiving radar returns and providing terrain and/or obstacle alerts or warnings in response to the radar returns. The electronics receives information from a database and the information is utilized to suppress false alerts or warnings.

Abstract: 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.

Abstract: A piloting method and device avoiding the Pilot Induced Oscillations. According to the invention, a piloting order (?) is filtered by means of a non-linear filter (12), the filtering function of which is controlled by speed comparison information.

Abstract: A driver assistance system for a vehicle includes an imaging device and an image processor operable to process image data captured by the imaging device. The driver assistance system may display information including the speed limit for the road along which the equipped vehicle is traveling and at least one of the speed of the equipped vehicle and a difference between the speed of the equipped vehicle and the speed limit, An adaptive speed control system may adjust the speed of the equipped vehicle responsive to at least one of (a) a speed limit for the road along which the equipped vehicle is traveling, (b) recognition of a warning sign at least in part by processing image data by the image processor and (c) detection of a curve in the road ahead of the equipped vehicle at least in part by processing image data by the image processor.

Abstract: Techniques for representing a holding pattern on a vertical situation display are described. The vertical situation display has a first screen area to depict the holding pattern and second screen area to show a flight path after the holding pattern. The representation of the holding pattern visually informs a flight crew of current and prospective flight conditions.

Abstract: A control method comprises calculating a target value for at least one of a plurality of control parameters of a control target. The method also comprises performing feedback control of the control target in order for a value of a first of the control parameters to be set closer to its target value, and adjusting a target value of a second of the control parameters based at least in part on a deviation between the target value and a current value of at least one of the other control parameter.

Abstract: The disclosed embodiments concern a process for limiting the control surface steering angle of an aircraft, including operations to: determine the maximum permissible steering angle in function of the speed of the aircraft, detect a yaw configuration of the aircraft following a first order for control surface deflection at a maximum steering angle and a first direction, apply a limit to the maximum permissible steering angle. The disclosed embodiments also concerns a system for implementing the process.

Abstract: A method and system for assuring separation between an aircraft and potential flight hazards is provided. According to the method, an intended path of the aircraft is predicted. A potential hazard to the aircraft along the intended path is identified. A distance from the potential hazard that the aircraft is required to maintain is determined. An ability of the aircraft to maneuver to avoid the identified hazard and to remain further from the identified hazard than the distance is determined. A probability that the aircraft will not maintain the distance from the identified hazards is determined. A pilot of the aircraft is alerted if the probability is greater than a predetermined level.

Abstract: Method and system for monitoring and analyzing, in real time, variation with time of an aircraft flight parameter. A time-dependent recovery band, defined by first and second recovery band boundaries that are spaced apart at at least one time point, is constructed for a selected flight parameter and for a selected time recovery time interval length ?t(FP;rec). A flight parameter, having a value FP(t=tp) at a time t=tp, is likely to be able to recover to a reference flight parameter value FP(t?;ref), lying in a band of reference flight parameter values FP(t?;ref;CB), within a time interval given by tp?t??tp?t(FP;rec), if (or only if) the flight parameter value lies between the first and second recovery band boundary traces.

Abstract: A method of diagnosing a turbine engine includes the steps of acquiring engine operating parameters; calculating corresponding engine residual values; computing the mean and the standard deviation of each engine residual value; normalizing dynamically each engine residual value to yield normalized engine residuals; mapping, via a cluster technique mapping, the normalized engine residuals as input vectors into an engine condition space having clusters representing either normal vector engine conditions or faulty vector engine conditions; and identifying a closest cluster within the engine condition space to determine whether the engine under analysis is normal or faulty. A belief factor may be obtained as a function of the distances between the input vectors and specific clusters.

Abstract: In one embodiment of a method for reducing vertical position errors of an aircraft, the displacement of the aircraft from a commanded vertical path may be determined. A determination may be made as to whether a magnitude of a vertical path error meets criteria. No more steps of the method may be followed if the vertical path error does not meet the criteria, while the vertical path error may be converted into a delta lift command if the vertical path error meets the criteria. The delta lift command may be limited. The delta lift command may be converted into lateral surface position commands for control surfaces. The lateral surface position commands may be communicated to lateral control surface actuators to move the control surfaces according to the lateral surface position commands.

Abstract: A field unit for warning of a danger of collision between an aircraft and an obstacle, in particular a topographical ground obstacle or an obstacle formed by a mast, building or aerial cable structure, comprises a multi-part tubular mast having devices for fixing a solar panel and a radar antenna; an elongate radar antenna in an environment-protective casing, which, with an electronics unit, forms a radar system for synthesized radar detection of an aircraft in a radar coverage area; a central processing unit for identifying on the basis of information from the radar system an aircraft which is in a zone of the radar coverage area and which on the basis of radar information such as direction, distance and/or speed computes a collision danger area; and a high-intensity light system and radio transmitter system that can be activated by the central processing unit upon detection of an aircraft in a collision danger area.