Abstract: Methods of predicting a speed brake fault in an aircraft having a speed brake system including multiple control surfaces, a handle for setting the position of the multiple control surfaces, and at least one control surface position sensor, the methods include receiving a position signal from the at least one position sensor, determining a variation in the position signal and predicting a fault in the speed brake system.

Abstract: This disclosure relates to a system for preventing collisions with a terrain. The system includes a detecting means for detecting risks of collision with the terrain after a predetermined forecasting delay. The system further includes a determining means for determining, based on a trajectory followed by the aircraft, a possible limit point for success of the vertical terrain avoidance maneuver. The system further includes indication means for giving indications on azimuth clearance sections, around the direction in which the aircraft is moving, suitable for success of the vertical terrain avoidance maneuver. The system further includes means for estimating a free-travel distance in each azimuth clearance sector on a straight distancing trajectory with constant gradient and over a distance correspond to more than one minute of flight, the free-travel distance being free of potential conflicts with the terrain.

Abstract: Described is a method of protecting an aircraft in approach by signalling against risks of collision with a terrain in steep-sided environments in order to avoid unwanted warnings emanating from clearance sensors of the on-board TAWS (Terrain Awareness and Warning System) while protecting the aircraft when the aircraft fails to observe a published procedure which includes a landing procedure and a take-off procedure. The method, in some embodiments, includes modifying characteristics of at least one of the clearance sensors according to the position deviation of the aircraft relative to a published RNP (Required Navigation Performance) trajectory.

Abstract: Methods and apparatus are provided for an actively variable shock absorbing system for actively controlling the load response characteristics of a shock absorbing strut. In one embodiment the shock absorbing system comprises a controllable valve adapted for actively varying a load response characteristic of the shock absorbing strut. The shock absorbing system further comprises an electronic control system comprising an input for receiving a signal from a sensor, an algorithm adapted to determine an optimal position for the controllable valve in view of the sensor signal, and an output for sending a control signal to the controllable valve to place the valve in the optimal position.

Abstract: A schematic display for presenting vertical navigation (VNAV) data is disclosed. A planned route such as a flight plan is divided into a series of VNAV legs, and only a VNAV schematic that corresponds to the active VNAV leg is displayed. The VNAV schematic in accordance with the present disclosure is a profile-view schematic for the active VNAV leg, providing a visual representation indicating the locations of the upcoming Top of Climb (TOC) or Top of Descent (TOD). Additional VNAV data may also be presented to provide content context. Since the schematic display in accordance with the present disclosure only displays VNAV data relevant to the active VNAV leg at a given time, the complexities associated with displaying the VNAV schematic is reduced, making the VNAV data easy to read and understand.

Abstract: A method and system for navigating an unmanned aerial vehicle (UAV) for aerial refueling is described. A system processor in the UAV receives navigation data from a tanker aircraft and calculates a plurality of relative navigation solutions with respect to the tanker aircraft. The system processor compares the plurality of relative navigation solutions to identify any inconsistent solutions. The inconsistent solutions are discarded and the system processor navigates the UAV in position for refueling using the remaining relative navigation solutions.

Abstract: A power electronic control circuitry device comprises the following intercommunicating distinct hardware physical entities: a digital microcontroller unit (UNMC) for managing the operation of the device, hardened to withstand the effects of radiations in space; a digital fast regulation unit (UNRR) for controlling priority and real-time processes, hardened to withstand the effects of radiations in space; a digital communication unit (UNC) for communications external to the device, hardened to withstand the effects of radiations in space; a digital tracing and debugging unit (UNTD) for detecting errors in the design of the device; and a digital non-volatile memory (MRN) for storing information representative of the initial configuration of the device, hardened to withstand the effects of radiations in space.

Abstract: An aircraft traffic alert system that minimizes false alarms and unnecessary alerts by automatically adjusting the sensitivity of the system based on proximity to an airport. The system also can use information from a flight management system (FMS) or GPS navigation system (GNS) to only adjust the sensitivity near a destination airport and to suppress potential alerts for possible collisions with other aircraft that will be moot based on planned course changes of the subject aircraft. The system also can suppress alerts related to another aircraft when the other aircraft is landing on a parallel runway to the runway on which the subject aircraft is landing. The system may use multiple sensitivity levels based on different airspace classes, each class being associated with a different sensitivity level.

Abstract: The invention relates to a flight management system for aircraft which makes it possible to carry out tests of the results of the calculations of the main functions for formulating the flight plans and trajectories of the aircraft making it possible to anticipate errors in this formulation, to present them to the crew as a function of criticality criteria, to store them so as to be communicated and processed by the maintenance teams.

Abstract: Systems and methods are disclosed for displaying the current trends (i.e., turning or going straight) or the future positions of vehicles of interest on a traffic display unit. The position, orientation and geometry of the displayed symbology is a function of parametric information broadcast by the vehicles of interest and processed by a computer system that controls the traffic display unit. In particular examples disclosed herein, the traffic display unit is a navigation display on an aircraft or a traffic display unit at a traffic controller's station. However, the methods disclosed herein have application to vehicular traffic other than aircraft, such as boats or ships.

Abstract: A method and apparatus for managing a touch screen system. Data generated by an acceleration detector about acceleration of the touch screen system is received. The acceleration detector is located within the touch screen system. An action is initiated by an input manager when the acceleration of the touch screen system reduces usability of the touch screen system.

Abstract: 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.

Abstract: A system is provided for monitoring an energy height of an aircraft during landing. The system includes a database including landing distance data; a processing unit configured to receive the landing distance data from the database and to calculate a landing distance of the aircraft based on a velocity and a height of the aircraft, the processing unit further configured to provide display signals based on the landing distance; and a visual display coupled to the processing unit and configured to provide a visual image based on the display signals.

Abstract: A device includes means for generating and applying to an aircraft protecting orders avoiding a flight with an excessive descent rate. More specifically, the device includes components configured to perform a series of operations including measuring the current vertical speed and the current height of the aircraft and comparing these flight parameters with a safety envelope defining couples of vertical speed and height that are indicative of an excessive descent rate. If the current vertical speed and height are located in the safety envelope, a protection is triggered by generating protecting orders to remove the aircraft from the safety envelope and applying those protecting orders to control surfaces of the aircraft.

Abstract: A system having a first motion sensor configured to sense movement of an object on a first side of a portal, the object including an RFID tag, a first RFID reader being activated by the first motion sensor when the first motion sensor senses movement of the object, the first RFID reader reading the RFID tag, a second motion sensor configured to sense movement of the object on a second side of the portal and a second RFID reader being activated by the second motion sensor when the second motion sensor senses movement of the object, the second RFID reader reading the RFID tag, wherein, when one of the first and second motion sensors sense movement of the object, the other one of the first and second motion sensors is deactivated for a predetermined period of time.

Abstract: A method and apparatus diagnoses a correct operation of a phase or star point isolation relay in an electric power steering system of the kind including a motor drive circuit and at least one phase isolation relay which connects a part of the drive circuit to a phase of the motor. The relay is opened during shutdown to isolate the motor phase from the part of the drive circuit and is normally closed during operation of the motor to connect the phase to the part of the drive circuit.

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: A system and method display general terrain clearance awareness, whether the aircraft is off route, on airway, off procedure, or on procedure, so altitude thresholds are not violated and EGPWS alerts are avoided, while reducing clutter in displaying the information. Altitude, location, and rate of change in altitude are considered in determining whether the aircraft will exceed the threshold altitude. A flight path or an area to be entered is highlighted when the threshold altitude will be violated by the aircraft with the current flight path. The threshold altitude may be a minimum or maximum allowed altitude, or the terrain.

Abstract: A method and apparatus for displaying an energy state of an aircraft. The energy state of the aircraft is identified by a processor unit based on a speed of the aircraft and an altitude of the aircraft. An indication of the energy state is displayed by the processor unit.

Abstract: A method and apparatus are present for monitoring a runway. Data is received about the runway from a number of sensors associated with an aircraft while the aircraft performs an operation on the runway. A number of conditions are identified for the runway using the data received from the number of sensors.

Abstract: An exemplary embodiment relates to an aircraft system for detecting wires. The system includes a processor configured to actively sense a presence of a first object and a second object. The processor determines a location of the first object and the second object. The processor determines a potential location of a wire between the first object and the second object. The processor actively senses the wire by providing electromagnetic energy to the potential location.

Abstract: The present invention is directed to providing takeoff rotation guidance. A takeoff rotation guidance indicator, including an aircraft reference symbol and a guidance cue, is displayed on a HUD (Head-up Display) of a HGS (Head-up Guidance System). The guidance cue is positioned in relation to the aircraft reference symbol based on a takeoff rotation pitch guidance and a takeoff rotation roll guidance. Thus, pitch and roll guidance information is simply communicated to the pilot of an aircraft. The takeoff rotation pitch guidance and the takeoff rotation roll guidance are calculated differently at different points during takeoff. In an alternative embodiment, the takeoff rotation guidance indicator includes a slip-skid symbol. The slip-skid symbol is positioned relative to aircraft reference symbol, but is displaced by the lateral acceleration of the aircraft. Thus, slip/skid guidance information is simply communicated to the pilot of an aircraft.

Abstract: Present novel and non-trivial methods for presenting traffic information are disclosed. In a first method, data representative of ownship position, first traffic, and second traffic are received by a traffic symbology generator (“TSG”). The traffic is divided into zones and a correlation between the targets of the traffic is determined. A traffic symbology data set is generated by the TSG based upon the results of the correlation(s). In a second method, data representative of ownship position and first traffic, runway references, and a selectable display range are received by the TSG. The traffic is divided into zones, and a traffic symbology data set is generated by the TSG thereafter. In a third method, data representative of ownship position and first traffic are received by the TSG. The traffic is divided into zones, and a traffic symbology data set is generated by the TSG thereafter.

Abstract: There is provided an avionics system that provides several avionics functions within a single LRU. In one embodiment, the system comprises a software-configurable RF assembly, one or more processor assemblies that are configured to provide multiple TAWS/TCAS/Mode S/ADS-B/ATC functions, interfaces to allow connections to aircraft electronics and data loaders, and multipurpose antennas. In one embodiment, a common processor architecture allows generic avionics processors to be configured to operate a number of TAWS/TCAS/Mode S/ADS-B/ATC functions without the need for multiple LRUs, and software-defined RF functions allow RF circuitry that interfaces to the processors to handle current and future communication needs.

Abstract: Methods and systems are provided for monitoring an aircraft. An exemplary method involves capturing, by a computing system at a ground location, a flight tracking image associated with the aircraft that is displayed on a first display device at the ground location, and communicating the captured flight tracking image to the aircraft for display on a second display device onboard the aircraft.

Abstract: A system and methods for generating alerts in a terrain awareness and warning system (“TAWS”) in an aircraft, using data acquired from a forward-looking radar The system comprises a forward-looking imaging device, an airport database, a navigation system, a forward-looking terrain alert (“FLTA”) processor, and a crew alerting system. The FLTA processor determines a measured clearance altitude of a highest cell within an area and compares it with a required minimum clearance altitude; if the measured altitude is equal or less than the required altitude, the crew is alerted. Alternatively, a terrain database may be used. with the FLTA processor for determining if the aircraft descends below the minimum operating altitude or is predicted to do so and then generating an alert. A method is disclosed for generating TAWS alerts using elevation angle measured by the forward-looking radar and terrain data retrieved from a terrain database.

Abstract: A method for automatically detecting an erroneous height value supplied by a radio altimeter mounted on an aircraft. The method includes measuring, during the aircraft's approach phase with a view to landing, the duration between the times when a first predetermined altitude threshold and a second predetermined altitude threshold are reached. This duration is measured by taking into account current height values supplied by the radio altimeter. The method then includes comparing the measured duration to a predetermined duration reference time, which is lower than a flight duration that would allow the aircraft to descend from the first predetermined altitude threshold to the second predetermined altitude threshold at a maximum vertical speed. An erroneous height value is detected if the measured duration is lower than the predetermined duration reference time.

Abstract: A method for velocity profile based approach to point control for an aircraft includes determining a distance from the aircraft to a target point; determining a velocity command based on the distance to the target point and a desired acceleration; and issuing the velocity command. A velocity profile based approach to point control module for an aircraft and a computer program product comprising a computer readable storage medium containing computer code that, when executed by a computer, implements a method for velocity profile based approach to point control are also provided.

Abstract: Method and device for aiding the piloting of an airplane during a landing phase for ensuring, during rollout on a landing runway, that in the nominal case the airplane will stop level with a selected exit, while guaranteeing that in the case of a fault the airplane will stop before the end of the runway.

Abstract: A display system and method for providing a display. A display system includes a computer processor, the computer processor being configured to receive information from a plurality of sensors. The computer processor is further configured to detect an abnormal situation, based on information received from the plurality of sensors. The display system further includes a database including abnormal situation response procedures in operable communication with the processor, wherein the database is configured to provide the processor with the abnormal situation response procedures upon the detection of an abnormal situation. The display system further includes a display device in operable communication with the processor, wherein the display device is configured to display information from the sensors regarding the abnormal situation and the abnormal situation response procedures.

Abstract: The present invention relates to a method and a device for centralized management of tasks to be carried out by a crew in the course of an aircraft flight. The method uses onboard navigation aid systems, such as a flight management system, a system for managing in-flight alerts for the implementation of the following steps: creation of a task by the flight management system; scheduling of the tasks by a system for managing alerts; and task execution by the system for managing alerts.

Abstract: A method and apparatus in a vehicular telemetry system and a remote data analysis system for detecting an event and switching a data acquisition mode. Checking a state of a data acquisition mode. If the state is in a filtered data state and if an indicator value is at or above a threshold value, then switch the data acquisition mode to an unfiltered data state and acquire unfiltered data. If the data acquisition mode is in an unfiltered data state and if the indicator value is below the threshold value, switch the data acquisition mode to a filtered data state and acquire filtered data.

Abstract: The method of identifying a flight profile of an aircraft, the aircraft including a centralized maintenance system and an item of equipment including a component designed to measure the environmental conditions, comprises: a first step of collecting data measured by a sensor of the component; a second step of comparing values measured by at least one sensor with predefined threshold values so as to store in a resource the values that exceed the threshold values; a third step of comparing at least one set of stored values with at least one predefined flight profile, a flight profile representing a trend of values measured by a sensor according to at least one item of information defining a flight context; a fourth step of identifying the flight profile that is closest to the set of values stored for a sensor.

Abstract: In a centralized navigation information management system installed on board an aircraft which is in a current position at a current time, the aircraft having a warning management system and a route management system with means for creating a route plan, the route plan having a future route plan corresponding with the part of the route plan beginning at the current position and at the current time, the system includes: means for creating a task comprising at least one task parameter relating to an item of navigation information, including a task variable corresponding to a condition of execution of the said task, the means for creating a task having means for determining a predicted time meeting the execution condition; and means for detecting a possible inconsistency between the created task and the route plan or the future route plan and for transmitting, when an inconsistency is detected, a message relating to the inconsistency to a first display means of a centralized warning management system to display

Abstract: 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.

Abstract: In a method for operating a number of control units including a central control unit which has a central wakeup functionality units, at least one control unit requests a wakeup signal for at least one future instant from the central control unit, and the at least one control unit is informed and awakened by the central control unit when the at least one instant is at hand.

Abstract: A monitoring device automatically monitors lateral guidance orders of an aircraft. The device includes a failure monitoring device for implementing comparisons between roll control orders generated by a number of equipments in order to be able to detect a failure of one of the equipments concerning the generation of lateral guidance orders of the aircraft. Additionally, the device includes a failure anticipation comparator device for analyzing inlet parameters of the equipments to determine when a failure of one of the equipments should be anticipated.

Abstract: The present invention relates to a system (1) and an associated method for managing audio warning messages in an aircraft. The system (1) comprises a plurality of monitoring systems (10, 20) capable of detecting the establishment of at least one warning condition (CA), and comprises a central broadcasting module (40), to which each of the monitoring systems is connected and which is capable of broadcasting an audio message (SIG) corresponding to a detected warning condition. In particular, in this system (1), the said central broadcasting module (40) comprises means (402, 420) for determining at least one priority warning condition among the warning conditions detected by the monitoring systems, and means (410, 430) for generating at least one audio message (SIG) corresponding to the at least one determined priority warning condition, in order to broadcast it.

Abstract: A method, system or computer usable program product for porting driver preferences between vehicles including initiating a first communication session between a computer in the first vehicle and an external device, receiving a driver profile from the first vehicle in the external device, wherein the driver profile was used to configure warnings and other driver settings in the first vehicle, initiating a second communication session between the external device and a computer in a second vehicle, transferring the driver profile from the external device to a second memory in the second vehicle, and using the driver profile to configure warning and other driver settings in the second vehicle.

Abstract: The present invention relates to a method for replacing legs in an air navigation procedure described as a series of legs, the legs forming part of an initial family of legs. The method includes: a step of determining a restricted family of legs included in the initial family of legs, so that each leg not belonging to the restricted family corresponds to a combination of legs belonging to the restricted family: The method also includes: a step of replacing in the navigation procedure the legs not belonging to the restricted family with combinations of legs belonging to the restricted family.

Abstract: A system may include a sensor for coupling with a vehicle configured for atmospheric flight. The sensor may be configured for detecting a turbulence event, where the turbulence event is at least one of experienced by the vehicle or occurs proximal to the vehicle during atmospheric flight. The system may also include a transmitter coupled with the sensor. The transmitter may be configured for automatically remotely transmitting data regarding the turbulence event to a ground based entity.

Abstract: A feathering, flapping and rotor loads indicator for use in a rotorcraft includes a calculation unit configured to calculate (a) a current temperature of a bearing of the rotor assembly using a first calculation model, (b) a projected temperature of the bearing using the first calculation model and (c) a load exerted on a selected component of the rotor assembly using a second calculation model, the first and second calculation models adapted to calculate, respectively, the projected and the current temperatures of the bearing and the load exerted on the selected component based on flight control parameters; and a display unit configured to display on a common scale a movable indicator, the movable indicator being driven by the highest value between the projected temperature of the bearing and the load exerted on the selected component. The display unit displays another movable indicator driven by the current temperature of the bearing.

Abstract: A method for controlling speed of an aircraft in the air. The method compares a variation of the aircraft speed in the air with a variation of the aircraft speed on the ground for an identical period, and detects any significant difference between the variations.

Abstract: A system includes an unmanned aerial vehicle (UAV) configured to be equipped with data representing a first UAV flight plan, and a ground station configured to control the UAV. The ground station is operable to receive, at a first time, a first data set representing at least one flight path of at least one aircraft, calculate a second UAV flight plan to avoid the at least one flight path of the at least one aircraft, the second UAV flight plan being based on the data representing the first UAV flight plan and the first data set representing at least one flight path of the at least one aircraft, and transmit data representing the second UAV flight plan to the UAV.

Abstract: A hybrid vehicle is driven by a power unit which includes: a first rotating machine including a first rotor, a first stator, and a second rotor, wherein the number of magnetic poles generated by an armature row of the first stator and one of the first rotor and the second rotor are connected to a drive shaft; a power engine, wherein an output shaft of the power engine is connected to the other of the first rotor and the second rotor; a second rotating machine; and a capacitor. A traveling mode of the hybrid vehicle includes an EV traveling mode and an ENG traveling mode, wherein the hybrid vehicle travels with a motive power from at least one of the first rotating machine and the second rotating machine in the EV traveling mode, and the hybrid vehicle travels with a motive power from the power engine in ENG traveling mode.

Abstract: An electronic multi-function probe (MFP) is provided for positioning adjacent an aircraft skin. The electronic MFP includes a plurality of pressure sensing ports and an electronics housing. Positioned within the electronics housing are air data processing circuitry and stall protection system processing circuitry. The air data processing circuitry is configured to generate air data parameters, including airspeed and altitude, as a function of pressures at the plurality of pressure sensing ports. The stall protection system processing circuitry of the electronic MFP is configured to detect stall conditions as a function of angle of attack and at least one air data parameter from the air data processing circuitry, and to generate stall protection system outputs indicative of the detected stall conditions.

Abstract: The present examples provide circuits, systems, processes, and the like for providing precision course guidance, typically for improved positive course guidance below published minimum descent altitude or decision altitude, including just in time calculations of obstacle free flight paths. The calculated flight path may be presented in the context of a synthetic scene of the environment surrounding the aircraft. To provide precision course guidance, exemplary avionics systems, processes and the like, as described below may be utilized.

Abstract: A method is provided for dynamically consolidating items of an aeronautical procedure in order to present to the operator the best action to perform according to the context of all the systems, in order to reduce his cognitive workload faced with an action to be carried out. The method consists, for each item of a procedure, in determining the text of the requested action, in choosing the text of the corresponding response that the crew must perform according to the general state and the configuration of the aircraft, in incorporating in the corresponding item the texts of the requested action and of the corresponding response, in displaying this duly enriched item, in detecting whether the requested action has indeed been accomplished and in displaying the result of this detection.

Abstract: Avionics display system is provided for deployment onboard an aircraft and includes an air traffic data source that provides the avionics display system with data indicative of at least position and velocity of a neighboring aircraft. The system comprises a cockpit display system, and a monitor included within the cockpit display system. The cockpit display system receives and displays position and velocity data pertaining to the neighboring aircraft on the cockpit monitor as a position symbol and a velocity vector graphic. A processor operatively coupled to the monitor is configured to generate an air traffic display on the monitor including symbology indicative of (1) the current position of the neighboring aircraft (2) a velocity of the neighboring aircraft, and (3) the rate-of-change of the velocity of the neighboring aircraft.

Abstract: Methods, systems, and computer-readable media described herein provide for filtering relevant traffic from sensed or received traffic information for display, enhancement, or alerting, without requiring knowledge of runway, taxiway, or taxi route locations at an airport. Traffic information is sensed or received regarding nearby aircraft or other vehicles and is filtered using one or more filtering strategies to determine a subset of relevant traffic for which to display traffic indicators and/or traffic data on a display unit in the aircraft. The subset of relevant traffic may be further tested for convergence or potential convergence and filtered using one or more additional filtering strategies to determine traffic having critical traffic conditions for which to enhance the display of the traffic indicators on the display unit or to alert the flight crew of the critical traffic conditions.