Abstract: A method of creating at least one flight plan of an aircraft includes entering a creation objective which illustrates a type and general characteristics of the flight plan to be created, automatically generating a flight plan outline, automatically generating a targeted request for information relating to missing parameters, entering the requested information relating to the missing parameters, and supplementing automatically the flight plan outline and automatically deleting any discontinuities to create, in a definitive manner, the flight plan.

Abstract: A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available.

Abstract: A system for activating the distress beacon determines a positional difference between a theoretical position of the aircraft determined from data of the flight plan and a real position of the aircraft determined from the navigation and monitoring equipment installed in the aircraft. This system delivers an instruction to arm the distress beacon when one or more conditions are met, among which is the condition that the positional difference exceeds a predetermined value.

Abstract: Local wind fields can be predicted if both the airspeed and the ground speed of the helicopter are known. An aircraft that uses an inertial navigation unit, autopilot and estimator allows a measure of ground speed to be known with good certainty. The embodiments herein extends this system to allow an estimate of the local wind field to be found without actively using an airspeed sensor, but instead combining the measurements of an accelerometer and a drag force model and a model of controlled aerodynamics of the aircraft to estimate the airspeed, which again can be used to estimate the local wind speed.

Abstract: A method of using LIDAR on an airborne vehicle is described. A beam of radiation is transmitted to target areas at least one of above, below, and in front of the airborne vehicle, the target areas including particles or objects. Scattered radiation is received from the target areas. Respective characteristics of the scattered radiation are determined. An air turbulence factor or characteristics are determined from the respective characteristics. The airborne vehicle is controlled based on the air turbulence factor, such that turbulence experienced by the airborne vehicle is minimized. Alternatively, the airborne vehicle is controlled based on the characteristics to avoid colliding with the one or more objects. In another example, the airborne vehicle is controlled based on the characteristics to reduce headwind or increase tailwind, and substantially reduce a carbon footprint of the aircraft.

Abstract: A on-aircraft computer device predicts aircraft states (e.g., altitude, speed, flight path angle, and fuel consumption) at any given time, while utilizing a Deterministic Genetic Algorithm to search 4-D flight path candidates that can comply with all path constraints to produce a feasible 4-D path candidate as a final OPD flight path to arrive at a metering waypoint in a specified time window.

Abstract: A plurality of wireless engine sensors each sense an engine parameter as engine data and transmits wirelessly the engine data regarding the sensed engine parameters and receives data regarding a sampling rate. An engine monitoring module is mounted at the aircraft engine and a wireless sensor transceiver is configured to receive the engine data regarding sensed engine parameters from the wireless engine sensors. A first wireless transmitter is carried by the housing. A memory is carried by the housing. A processor is coupled to the memory, sensor transceiver and the first wireless transmitter and collects and stores in the memory engine data relating to engine parameters and transmits the engine data via the first wireless transmitter.

Abstract: A method of transferring aircraft data from an aircraft to a portable electronic device entails receiving at the portable electronic device the aircraft data from a data connection with an aircraft data source without writing data back to the aircraft or from a user interface while being capable of receiving aircraft data via the data connection and executing an application on the portable electronic device using the aircraft data to present new information about the aircraft or its operating environment that is not available for display on a cockpit display but which is displayable on the portable electronic device based on the aircraft data received by the portable electronic device.

Abstract: A method to develop a system for management of warnings and electronic procedures for an aircraft, comprising a database of parameters relating to the warnings and to logic and procedures, the aircraft comprising ATA equipment, comprises definition and calculation of maturity criteria for development of the system, which comprises, in order: A) verification of warnings in the database with respect to predefined lists of warnings and calculation of a maturity criterion, B) if the criterion of A>predetermined threshold, verification of the coherence of the logic for the warnings then definition and calculation of a maturity criterion, C) if the criterion of B>predetermined threshold, verification of the existence of the procedures and, for each warning, analysis of its logic with respect to its procedure, then definition and calculation of a maturity criterion, the system being fully set up when the latter criterion>predetermined threshold.

Abstract: A method and apparatus for providing assistance to a flight crew during flight. An image of a group of instruments on a flight deck of an aircraft is generated with an image sensor in a data processing system. Assistance information configured to assist the flight crew from flight information displayed by the group of instruments in the image is generated. The assistance information is displayed on a display device in the data processing system.

Abstract: A present novel and non-trivial system, device, and method for presenting winds aloft symbology on an aircraft display unit are disclosed. Symbology image data representative of a plurality of sets of winds aloft symbologies may be generated as a function of flight plan data and weather data; flight plan data representative flight plan comprised of a plurality of waypoints may be received along with weather data representative of winds aloft data corresponding to each waypoint. Each set of winds aloft symbologies may be comprised of winds aloft symbology corresponding to each waypoint of the flight plan at a single altitude and symbolize winds aloft at that altitude. When provided to a display unit, each set of winds aloft symbologies represented in the symbology image data may be presented in a series of increasing or decreasing altitudes, where the series is presented sequentially or simultaneously.

Abstract: A device aiding the flight management of an aircraft during a phase of landing on an airport includes means for automatically determining an adaptive aiming point that is shifted along the runway in the downstream direction and which can be used by different usual landing aid means of the aircraft.

Abstract: The present invention relates to a method for detecting the performance of the aircraft comprising: collecting data reflecting operation status of the aircraft; generating the customized message based on the collected data, wherein, the customized message is configured to include one or more main parameters related to the operation status of the aircraft; storing or transmitting the customized message; and detecting the performance of the aircraft based on the customized message.

Abstract: Methods and systems for a go/no-go Landing Decision Point (LDP) are disclosed. The methods and systems provide a graphical LDP on a cockpit display that pilots can use to determine whether to continue the landing or execute a go-around. The methods and systems may be implemented in embodiments having an onboard portion, an off-board portion, or both operatively coupled to provide an LDP in a preview/planning mode and real time mode.

Abstract: A system and method for assisting flight crew recovery in the aftermath of an unexpected event is provided. A processor is used to detect that an unexpected event has occurred in an aircraft and, in response to detecting that the unexpected event has occurred, state data are stored in memory. The processor is also used to detect that the unexpected event has been resolved and, in response to detecting that the unexpected event has been resolved, the processor retrieves the state data from the memory, generates an aftermath plan that includes prompts to guide the flight crew to complete the aftermath plan, and continuously updates the aftermath plan until the aftermath plan is completed.

Abstract: A method and a device are disclosed for exchanging data between a technical management system of an aircraft and a mission management system of the aircraft, in order to permit one of the systems to determine the consequences of an event detected in the other of the systems. After at least one event has been detected in one of the technical management and mission management systems of the aircraft, at least one information item pertaining to the detected event is transmitted to the other of the technical management and mission management systems of the aircraft. The consequences of the event detected in the other of the technical management and mission management systems of the aircraft are then determined. The adaptation of at least one datum of the other of the technical management and mission management systems of the aircraft is evaluated in response to the determination.

Abstract: A method for regulating an actuator for a control surface is provided, which actuator has an angular position controlled by an autopilot on an aircraft with mechanical flight control. When the value of the torque exerted by the actuator is less than a threshold torque value, the actuator is regulated in terms of position and the maximum speed of movement of the control surface is limited to a value that is dependent on the torque value. When the value of the torque exerted by the actuator is greater than the threshold torque value, the actuator is regulated in terms of torque.

Abstract: A system and method to display, when within an envelope of an ownship's flight path, a symbol representing wake turbulence from another aircraft based on aircraft type and flight parameters received from the other aircraft, the symbol being formatted to indicate the severity of portions of the wake turbulence. The format is modified periodically in accordance with the aircraft's flight path and a decay rate of the wake turbulence.

Abstract: An improved Horizontal Situation Indicator (HSI) module for use with an aircraft, wherein the HSI module is adapted for accepting Bank Angle Commands or waypoint data from the GPS flight module and for using the same to determine a heading error. The HSI module is further adapted for outputting the heading error to the Flight Director module where it can be used to create a Roll Command for output to the Auto-Pilot, whereby the Auto-Pilot can be commanded to follow a turn using the HSI and the Flight Director without requiring an additional module be added to the aircraft to create the heading error for use by the Flight Director. The waypoint data can be of the “flyover” type or the “flyby” type.

Abstract: An electronic flight control system for an aircraft capable of hovering and having at least one rotor. The flight control system is configured to operate in a manual flight control mode, in which the flight control system controls rotor speed in response to direct commands from the pilot; and in at least two automatic flight control modes corresponding to respective flight modes of the aircraft, and in which the flight control system controls rotor speed automatically on the basis of flight conditions. The flight control system is also configured to memorize, for each automatic flight control mode, a respective flight table relating different speed values of the rotor to different values of at least one flight quantity; and to automatically control rotor speed in the automatic flight control modes on the basis of the respective flight tables.

Abstract: A method of formulating a specification for temporal and vertical required navigation performance is described. The method assesses various flight management guidance systems methods and allows a specification to be set for an airport. The specification may be used to increase aircraft traffic into the airport. The specification sets limits on deviations in time and altitude, for example, on approach into arrivals at the airport. The method comprises: calculating temporal and vertical deviations from a reference trajectory for one or more flight management guidance methods for one or more aircraft types; and comparing the temporal and vertical deviations with operational requirements of the airport. The deviations from a reference trajectory may result from uncertainties affecting trajectory prediction, such as wind and temperature prediction accuracy.

Abstract: A visual/graphical air traffic display tool to aid flight crews in determining future heading/track and position of ownship based on current climb rate, bank angle and groundspeed under current meteorological conditions. The tool displays symbols which indicate the predicted future position and heading/track of ownship on a traffic display unit. The tool is also capable of using ownship's predicted position and information received from surrounding traffic to identify a future conflict at ownship's predicted position and then display a future conflict warning on the traffic display unit. In one embodiment, the future conflict warning takes the form of a change in the coloration of the ownship position and heading/track indicator being displayed.

Abstract: A method and apparatus for displaying aircraft information. A selection of a piece of dynamic information is detected about an aircraft on a first display on a user interface. The piece of dynamic information is used to operate the aircraft and changes during operation of the aircraft. The piece of dynamic information selected from the first display is added to a custom display on the user interface. The custom display is displayed on the user interface on a display system for the aircraft.

Abstract: The general field of the invention is that of devices for display and control of setpoints for automatic piloting for aircraft, configured to display the setpoints of speed, heading, climb slope and altitude. The various setpoints are displayed in the form of a graphical representation comprising: wheels graduated in speed and in altitude indicating the aircraft setpoint values; a circular heading rose, graduated and centered on a first symbol representing the aircraft, the heading setpoint being indicated by a second symbol representing the heading to be followed by the aircraft and disposed around the perimeter of the heading rose; and a vertical sectional view comprising a graduated semicircle centered on a third symbol representing the aircraft, the slope setpoint being indicated by a fourth symbol representing the slope to be followed by the aircraft and disposed around the perimeter of the semicircle.

Abstract: A system and method for identifying a recommended configuration for operating an aircraft in wind shear conditions. A processor unit receives information associated with an operation to be performed by the aircraft. The processor unit receives an indication that wind shear may be present during the operation. Responsive to receiving the indication that the wind shear may be present during the operation, the processor unit identifies the recommended configuration for the aircraft to perform the operation using the information associated with the operation to be performed by the aircraft and rules for operating the aircraft in the wind shear conditions.

Abstract: The invention relates to a device aboard an aircraft comprising output means configured to restore information relating to the aircraft status from aircraft systems, the device including a module providing interface between said output means and said aircraft systems, said module being configured to synthesize information from aircraft systems depending on predetermined behavior rules and to transmit said information thus synthesized to said output means.

Abstract: A system and method are provided for integrating and displaying the collective cue and the pitch and roll cue of a helicopter display with a flight path marker providing a moving reference showing the aircraft flight path.

Abstract: A method is provided for inferring the aircraft intent of an aircraft from an observed trajectory. Aircraft performance data relating to that type of aircraft is retrieved from memory, along with atmospheric conditions along the observed trajectory. An initial set of candidate aircraft intents is generated. Each aircraft intent provides an unambiguous description of how the aircraft may be flown that allows a determination of an unambiguous resulting trajectory. A computer system calculates a trajectory defined by each candidate aircraft intent and forms a cost function from a comparison of each calculated trajectory to the observed trajectory. An evolutionary algorithm evolves the initial candidate aircraft intents, wherein the evolutionary algorithm uses a multi-objective cost function to obtain a cost function value that measures the suitability of each candidate aircraft intent.

Abstract: Present novel and non-trivial system, device, and method for combining image data received from two or more vision systems are disclosed. A system may be comprised of a first vision source, a second vision source, and an image generator (“IG”). The first vision source may be could configured to generate a first image data set and a depth buffer data set, and the second vision data source could configured to generate a second image data set. The IG could be configured to receive both the first and second image data sets; the depth buffer data set; and generate a third image data set as a function of both image data sets, the depth buffer data set, and a pixel cutoff distance that may be fixed or variable. In addition, the pixel cutoff distance may be determined as a function of input variable data.

Abstract: An apparatus for generating flight-optimizing trajectories for a first aircraft includes a receiver capable of receiving second trajectory information associated with at least one second aircraft. The apparatus also includes a traffic aware planner (TAP) module operably connected to the receiver to receive the second trajectory information. The apparatus also includes at least one internal input device on board the first aircraft to receive first trajectory information associated with the first aircraft and a TAP application capable of calculating an optimal trajectory for the first aircraft based at least on the first trajectory information and the second trajectory information. The optimal trajectory at least avoids conflicts between the first trajectory information and the second trajectory information.

Abstract: Methods and systems for determining a change of speed of an aircraft for enabling the avoidance of conflicts between aircraft trajectories. The method of determining a change in speed of an aircraft, comprises the steps of: defining a merge point and a tie point; monitoring a first aircraft; determining when the first aircraft passes the tie point; providing trajectory data; predicting a trajectory of a second aircraft using the trajectory data; defining a minimum permissible longitudinal spacing; predicting a longitudinal spacing between the first and second aircraft at the merge point based on the predicted trajectory; and if the minimum permissible longitudinal spacing is greater than the predicted longitudinal spacing then calculating a proposed change in speed of the second aircraft that will result in the longitudinal spacing between the first and second aircraft at the merge point being greater than or equal to the minimum permissible longitudinal spacing.

Abstract: A method of predicting a horizontal stabilizer system fault in an aircraft, where the method includes receiving data relevant to a characteristic of the pitch of the aircraft during flight, comparing the received data to a reference pitch characteristic, predicting a fault in the horizontal stabilizer system based on the comparison, and providing an indication of the predicted fault.

Abstract: A technique for identifying, projecting, displaying, and enhancing the thermal capacity for an aircraft is disclosed wherein the thermal capacity is defined as the amount of time or range the aircraft can continue until a thermal limit is exceeded.

Abstract: A head-up display system includes an aircraft, a predicted flight path generation component that calculates a predicted flight path over a period of time, and a graphic generation component configured to generate a graphical display and project it onto a combiner configured to combine the graphical display with a visual exterior view. A synthetic vision system includes an aircraft, a predicted flight path generation component that receives one or more state parameters and calculates a predicted flight path over a period of time, and a synthetic terrain generation component configured to generate a synthetic view which is displayed on a display. The graphical display and/or the synthetic view includes a three-dimensional depiction of the predicted flight path over the period of time generated utilizing one or more three-dimensional transforms, one or more graphical images based on flight data, and a three-dimensional graphical depiction of a flight plan.

Abstract: A method and a device for protecting an aircraft in the flight phase, said aircraft exhibiting several configurations of slats and flaps, comprises the following steps: determining, for at least one configuration of slats and flaps, of a limit angle of incidence beyond which the aircraft runs a risk of stalling, determining a gain factor as a function of the normal acceleration of the aircraft, comparing the current angle of incidence of the aircraft with the limit angle of incidence weighted by the gain factor, and, emission of an alert indicating that the aircraft runs a risk of stalling, if the current angle of incidence of the aircraft is greater than the limit angle of incidence weighted by the gain factor.

Abstract: A present novel and non-trivial system, apparatus, and method is disclosed for presenting a flight director-dependent highway in the sky (“HITS”) pathway on an aircraft display unit. A processor receives flight plan data and flight director data, generates HITS data set representative of a flight director-dependent HITS pathway using flight plan data and flight director data, and provides the HITS data set to a display system for presentation of the flight director-dependent HITS pathway on a tactical display unit. Flight plan data provided to the processor may comprise of data sourced by a navigation system or HITS pathway data generated independently of flight director data. When presented on a tactical display unit, the flight director-dependent HITS pathway may be depicted with the flight director, where the proximal end of the HITS pathway aligns with the flight director.

Abstract: An aerological phenomena alert device for an aircraft, which comprises onboard equipment capable of detecting meteorological phenomena, comprises: a module for collecting and storing meteorological data originating from the onboard equipment capable of detecting the meteorological phenomena, a module for creating a report from the collected meteorological data, a module for sending the report, a module for receiving reports sent by surrounding aircraft, a module for processing and consolidating the reports received, and for generating alerts when a report signals an aerological phenomenon, and a module for merging the data originating from aircraft and from meteorological stations, situated in a station on the ground and comprising a ground/air communication module for sending meteorological reports adapted to each aircraft according to its position in relation to an aerological phenomenon.

Abstract: A method of providing maintenance to an aircraft having multiple aircraft systems and a method of operating an aircraft having multiple aircraft systems, with at least some of the aircraft systems outputting one or more visual indicia indicative of a status of a system of the aircraft where the method provides information based on such visual indicia. An aircraft system for at least one of operating and maintaining the aircraft, which may retrieve information based on such visual indicia.

Abstract: Systems and methods to mitigate instrument landing system (ILS) overflight interference are disclosed. An example method performing a first measurement of a position of an aircraft relative to a first location based on an instrument landing system, performing a second measurement of the position of the aircraft based on inertial measurements performed over a first time period occurring prior to the first measurement, performing a third measurement of the position of the aircraft based on inertial measurements performed over a second time period greater than the first time period and occurring prior to the first measurement, and generating guidance information based on a selected one of the first, second, or third measurements of the position of the aircraft.

Abstract: A computer-implemented system and method for the collection, filtering, and transmission of aviation information is disclosed. A plurality of flight information is received over a digital network at various remote locations, and the data is filtered prior to transmission to a central database for presentation and use. The database includes aviation information. The method of filtration is dynamically updated as to information concerning a specific flight based on one characteristic of the flight. As to aircraft being tracked, a determination is made as to which receiver should relay collected data, and that determination is periodically revised, such as to minimize transmission costs and maximize signal quality as aircraft positions change. Once the information is located in the central database, it is suitable for use in responding to user requests for flight tracking information is association with at least one identified flight.

Abstract: Methods and systems are provided for assessing a target proximate a vehicle. A location and a velocity of the target are obtained. The location and the velocity of the target are mapped onto a polar coordinate system via a processor. A likelihood that the vehicle and the target will collide is determined using the mapping.

Abstract: A highly reliable aerodynamic coefficient estimate can be computed, and computation of this aerodynamic coefficient estimate enables accurate detection of control surface failure/damage while reducing a discomfort for passengers. A deflection angle command signal generation means (5) generates a deflection angle command signal for estimating an aerodynamic coefficient indicating the aerodynamic characteristics of an airframe. A kinetic state quantity acquisition means (6) acquires a kinetic state quantity of the airframe that is obtained as a result of a control surface provided on the airframe being moved based on the deflection angle command signal. A candidate value calculation means (7) calculates candidate values for estimating the aerodynamic coefficient from the kinetic state quantity using two or more different estimations. An aerodynamic coefficient estimate determination means (8) determines an aerodynamic coefficient estimate based on the candidate values.

Abstract: The different advantageous embodiments provide a system comprising an environmental waypoint insertion process and a processor unit. The processor unit is configured to run the environmental waypoint insertion process. The environmental waypoint insertion process is configured to receive information. The environmental waypoint insertion process determines whether and how to suggest additional waypoints for insertion into a flight plan to a subscriber.

Abstract: An alerts and procedures management system for an aircraft comprises a software kernel aboard the aircraft and a parameterization tool for the software kernel, which comprises a conversion module for converting a configuration file describing an operational need of the system into a database of binary parameters which is able to parameterize the software kernel. The software kernel comprises at least four elementary cells: a first cell for acquiring aircraft signals, a second cell for characterizing state variables of the aircraft, a third cell for computing at least one separate event, a fourth cell for scheduling the separate events for communication with the crew; each of the cells comprising a software engine parameterizable by the database.

Abstract: A flight management system (FMS) including a plurality of FMS components that can include a civil FMS component and a tactical FMS component. Each FMS component can have a processor programmed to execute an FMS software product. The FMS can also include a multi core FMS manager configured to control a plurality of flight management systems and coupled to the plurality of FMS components. The multi core FMS manager can include a plurality of FMS managers, each coupled to one of the FMS components, and a platform interface manager coupled to an avionics system. Each FMS manager can be adapted to transmit flight management data to, and to receive flight management data from, the FMS component to which it is coupled. The platform interface manager can be adapted to provide each FMS component access to the avionics system, such that an aircraft operator can control each FMS component via the FMS.

Abstract: Method and device for an optimal management of the energy of an aircraft. The device (1) includes means (5) for determining, in an iterative manner, according to a predicted energy state and according to a management strategy, optimal commands of means (S1,S2, S3, S4, S5, S6) for controlling the energy of the aircraft, which allow the aircraft to reach a given point of a trajectory in a given operational state.

Abstract: Method of determining navigation parameters for a carrier by a hybridization device comprising a Kalman filter (3) formulating a hybrid navigation solution on the basis of inertial measurements calculated by a virtual platform (2) and of raw measurements of signals emitted by a constellation of satellites delivered by a satellite positioning system (GNSS), characterized in that it comprises, the steps of: —determination, for each satellite, of at least one likelihood ratio (Ir, Ir?) between a hypothesis regarding a fault of a given nature of the satellite and a hypothesis regarding an absence of fault of the satellite, —declaration, of a fault of a given nature on a satellite as a function of the likelihood ratio (Ir, Ir?) associated with this fault and of a threshold value, —estimation of the impact of the declared fault on the hybrid navigation solution, and ?correction of the hybrid navigation solution as a function of the estimation of the impact of the declared fault.

Abstract: Systems and methods for managing the exchange of vehicle information between software modules with different safety importance. In one embodiment, a vehicle health management system includes a mission critical software module, a flight critical software module and a gatekeeper. The mission critical software module receives vehicle state information and provides it to the flight critical software module if the gatekeeper confirms the validity of the vehicle information.

Abstract: Apparatus and methods for controlling a system that operates responsive to a plurality of input control signals are disclosed. During operation the system generates a plurality of output status/control signals. A master controller has at least first and second controllers. The first controller outputs and inputs signals over a first communication path, and the second controller outputs and inputs signals over a second communication path. The first and second controllers output signals based on input signals received over the first and second communication paths, respectively, and also based on stored control data. A plurality of input/output modules are provided. Each of the input/output modules has first and second slave controllers. The first slave controller of each of the input/output modules inputs and outputs signals over the first communication path to the first controller, and the second slave controller outputs and inputs signals over the second communication path.

Abstract: A procedure and a device for the determination of current airspeeds [13] of a rotorcraft [2] in a stationary flight regime and/or at low speeds. A calculation system [1] incorporates two pairs of polynomial calculation laws [9] [10] that are executable successively by pairs. A pair of first polynomial laws [9] calculates estimated airspeeds [11], consisting respectively of longitudinal and lateral airspeeds, and is constructed through multilinear regression based on parameters relating to simulated flight points [17] defined by means of a flight simulator [18]. A pair of second polynomial laws [10] calculates the current airspeeds based on the estimated airspeeds [11], and is constructed through multilinear regression based on parameters relating to test-flight points defined by means of test flights [25].