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: In a method for stand-alone alignment of an inertial unit for an onboard instrument capable of being mounted in an aircraft, the method includes monitoring the appearance of a movement of the inertial unit during the alignment, suspending the alignment of the inertial unit in the event of the appearance of movement, and resuming the alignment of the inertial unit on the disappearance of the movement.

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: A method and device for automatically estimating a degradation in fuel consumption and in drag of an aircraft. The device comprises a device for calculating a numerical value of the effect of a degradation in performance on the fuel consumption and/or the drag of the aircraft, and an arrangement for displaying this numerical value on a screen in the cockpit of the aircraft.

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].

Abstract: A method for estimating airspeed of an aircraft includes receiving values indicative of operating conditions of the aircraft along an axis; estimating a tip path plane (TPP) angle along the axis from at least one of the operating conditions to create an estimated TPP angle; and determining an estimated airspeed as a function of the estimated TPP angle, the determining including referencing a look-up table that indexes the estimated TPP angle with the airspeed.

Abstract: A flight control system for an aircraft, controlling a plurality of actuators adapted to actuate control surfaces of the aircraft, including: at least one communications bus; at least one computer situated in the avionics bay of the aircraft, and adapted to calculate flight commands and to transmit them over the bus in the form of command messages; and at least a first remote terminal connected to the bus, adapted to control a control surface actuator, and to acquire the state of the actuator from information provided by at least a first sensor, the first terminal receiving command messages from the computer and transmitting electrical orders to the actuator as a function of the command messages received in this way, and also transmitting messages to the computer, at its request, relating to the state of the actuator as a function of the information provided by the first sensor.

Abstract: A vehicle system for determining an object threat level, includes a display and electronics configured to receive mission context data indicating an operational state of the vehicle. The electronics determines a threat level of the object in response to the mission context data. The electronics determines at least one recommended action in response to the threat level. The electronics provides an indication of the threat level and at least one recommended action to the display.

Abstract: An improved stable approach monitor (SAM) system provides an audible advisory to a pilot when an aircraft is on a final landing approach. More specifically, the SAM system compares a measured airspeed of the aircraft to a predetermined flap placard speed. If the measured airspeed exceeds the predetermined flap placard speed then the improved SAM system provides an audible advisory indicating the airspeed of the aircraft is too fast. Advantageously, this audible advisory should prevent the pilot from attempting to deploy the flaps at an excessive airspeed and in turn focuses the pilot's attention on the problem at hand, which would be to reduce the airspeed of the aircraft. Once the airspeed is equal to or below the predetermined flap placard speed, the improved SAM system may provide another audible advisory informing the pilot to commence deployment of the flaps.

Abstract: A method of selecting weather data for use in at least one of a flight management system (FMS) of an aircraft and a ground station includes selecting a reduced set of weather data points to send to the FMS and taking into account a trajectory of the aircraft when determining what data points to include in the reduced set.

Abstract: The invention relates to a method for transmitting data, characterized in that it includes a step of transmitting in-flight data between a first aircraft and at least a second aircraft, the data transmitted being data stored in at least one black box on board the first aircraft.

Abstract: An installation for detecting and displaying the failures of the functional systems of an aircraft is described. The installation can include both a general alarm system (4) connected to said functional systems (2) and to the auxiliary alarm detection means (5) originated from said functional systems, and a complementary alarm system (6), connected to said functional systems (2), independently from the general system (4), and able to indicate a breakdown not detected by the general system on the instrument panel of the cockpit.

Abstract: An inclination control method using a torque vectoring system, may include a) detecting a vehicle speed, a steering angle, a yaw rate, and a steering torque of a vehicle, b) determining whether the vehicle may be tending to be inclined according to detected values of the vehicle speed, the steering angle, the yaw rate, and the steering torque, c) determining a torque vectoring duty according to the magnitude of the steering angle and the yaw rate when it may be determined that the vehicle may be tending to be inclined, and d) controlling the torque vectoring system according to the determined torque vectoring duty.

Abstract: An asset operational health monitoring system, in which a plurality of sensors are arranged to determine values of asset operation parameters pertaining to an instance of asset operation. One or more processing unit receives data corresponding to said asset operation values and determine a plurality of asset locations at a corresponding plurality of points in time. The one or more processing unit is arranged to receive data indicative of the location of a region of adverse environmental conditions which may impact on the operation of the asset and to compare the determined locations of the asset with the location of said region so as to determine whether one or more of said asset locations fall within said region. An indicator of operational risk associated with the presence of said asset in said region is output which can drive asset operation or maintenance decision making. The system may be used for ash cloud impact monitoring for aircraft, a fleet of aircraft or aircraft engines.

Abstract: A torque based power limit cueing system is provided and includes an engine computer to compile data relating to torque and additional information of each of one or more engines, an active stick by which tactile cueing are provided to a pilot and by which the pilot inputs control commands, a multi-function display (MFD) by which visible cues are provided to the pilot and a flight control computer (FCC) operably coupled to the engine computer, the active stick and the multi-function display, the FCC being configured to receive the data from the engine computer and to output tactile cue commands and visible commands in accordance with the torque and the additional information of each of the one or more engines to the active stick and the MFD, respectively.

Abstract: A method for aiding the management of an aircraft flight according to an active flight plan receiving a control clearance transmitted at a current time includes a step of computing a reception flight plan based on the said control clearance, a step of storing the said reception flight plan in a memory space dedicated to the said reception flight plan. The method also includes, prior to the step of computing a reception flight plan: a step of determining the time, called the recognition time, assumed to have to elapse between the current time and a time at which the said control clearance is assumed to be recognized; a step of attribution, to the said control clearance, of a destination flight plan as a function of the recognition time, the said destination flight plan being the temporary flight plan when the recognition time is included in a first time slot and the destination flight plan being a secondary flight plan when the recognition time is included in a second time slot longer than the first time slot.

Abstract: A method and apparatus for managing a flight of an aircraft. Conditions in an environment around the aircraft are monitored during the flight of the aircraft on a route having a number of target points. In response to detecting a condition requiring a change to the route of the aircraft, current resources for the aircraft are identified. A determination is made as to whether changing the route reduces the number of target points that can be reached based on the current resources for the aircraft. In response to a determination that changing the route reduces the number of target points that can be reached, the route is changed to include a portion of the number of target points using the condition and a policy.

Abstract: An aerodynamic state estimation system includes a real-time actual measurement device, an air data computer, and a plurality of sensors. The measurement device receives laser scatter energy indicative of one or more atmospheric data parameters and outputs one or more truth measurements. The air data computer module receives the one or more truth measurements, calculates one or more state parameter estimations based on a plurality of functional parameters, and outputs at least one of the one or more truth measurements and the one or more state parameter estimations as one or more high accuracy state parameters, The plurality of sensors, located at the air data computer module, measure the plurality of functional parameters.

Abstract: A runway indicator is displayed overlying a target runway for providing supplementary guidance to support the pilot's ability to fly a stabilized approach. The highlighted runway position indicator provides cues to verify that the aircraft is continuously in a position to complete a normal landing using normal maneuvering during the instrument segment of an approach and includes a landing threshold, a landing zone on the runway, an approach line leading to the runway, an outline highlighting the sides and ends of the runway, a rectangle larger than and surrounding the runway, and a visual precision path approach indicator.

Abstract: A data collection and distribution system for monitoring aircraft in flight, on the ground and at the gate or terminal for monitoring critical and catastrophic events, managing the emergency during such an event, and for investigating the event. The system generates, transmits and collects critical data generated by monitoring equipment onboard an aircraft or other commercial transport and selectively displays the data on a cockpit display console as well as for downloading, transmitting and displaying data at external monitoring and response stations, including fixed ground stations, roving ground stations and chase aircraft or vehicles. Digital surveillance information is collected, processed, dispatched, and log via remote control and access. The system includes a variety of system appliances such as surveillance cameras, sensors, detectors, and panic buttons and accommodates legacy equipment.

Abstract: A method for controlling the piloting of an aircraft comprising the steps of receiving at least one first instruction for modification of a current velocity vector of the aircraft, determining a target velocity vector of the aircraft, on the basis of said at least one first instruction received, and determining, on the basis at least of said target velocity vector, at least one actuation command intended for at least one actuator of the aircraft in order to modify the movement of the aircraft according to said at least one first instruction received.

Abstract: A method and hold path computation system for automatically generating a hold path for an aircraft flying in a holding pattern, wherein the holding pattern is defined by one or more orbits within a selectable holding area are provided. The system includes a processor configured to receive a hold departure time indicating a time the aircraft is to leave the hold path to meet a required time of arrival (RTA) at a waypoint, determine a present position of the aircraft within the holding pattern, and determine an amount of time to complete a current hold orbit. The processor is also configured such that if the determined amount of time to complete a current hold orbit is less than or equal to the hold departure time, maintain the aircraft flying in the holding pattern and determine an amount of time by which to shorten the next orbit to exit the holding pattern at the hold departure time.

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: The present invention relates to an on-board aeronautic system intended to be dynamically reconfigured, especially an on-board information system, and to an associated method as well as to an aircraft comprising such a system. In particular, the system comprises a plurality of heterogeneous equipment items, at least part of the said equipment items being reconfigurable, and comprises a reconfiguration management center set up to receive state messages from the said plurality of equipment items and to emit reconfiguration messages destined for the said reconfigurable equipment items as a function of at least the said received messages, the said state messages being emitted according to the same format by monitoring means encompassed in each of the said equipment items, the reconfigurable equipment items encompassing reconfiguration means capable of processing at least one of the said reconfiguration messages in order to reconfigure the said associated equipment item.

Abstract: The present application relates to a system and method for providing real-time indications of economic impact of aircraft operations to an aircraft operator. The system and method allow the aircraft operator to reduce economic impact during flight of the aircraft. Such an analysis and cue to the aircraft operator allows the operator to make real-time changes during flight to reduce damage of life-limited aircraft components, thereby reducing the economic impact of aircraft operation that is directly associated with maintenance and component replacement. The system and method can also include pre-flight and post-flight analysis methods for reduction of economic impact of flight operations.

Abstract: A multi-product avionics control and display unit (CDU). In implementations, the CDU may include a display and a processor coupled with the display. The processor is configurable to operate in a first mode to cause the display to present standby primary flight information associated with the aircraft and a second mode to control and display operation of one or more aircraft systems associated with the aircraft.

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 low-cost fleet operations quality management system for use with one or more vehicles which includes a data recording unit and separate memory subsystem mounted on each vehicle, a remotely located data collection station to collect, store and pre-process data from multiple vehicles, a centralized data storage and retrieval system designed to accept and assimilate recorded trip data, a web application designed to provide access to and analysis of the recorded trip data, and a graphical software application that can be used to view the recreated trip in a realistic simulated environment.

Abstract: Technologies are described herein for providing a list of alternate diversion airports that is based on up-to-date and accurate information received electronically at the aircraft. The list of alternate diversion airports may be prioritized according to a normal mode when the aircraft is operating under normal flight conditions, or a non-normal mode when the aircraft is operating in an emergency situation. In one aspect of the present disclosure, a system includes an alternate airport diversion planner program that generates the list of alternate diversion airports based on diversion planning information received at an aircraft. The alternate airport diversion planner program subsequently receives periodic updates of the diversion planning information, which is used to update the list of alternate diversion airports that is provided to a pilot of the aircraft.

Abstract: According to the invention, during take-off, the aircraft (AC) is given the tail strike attitude (?ts) and the ailerons (6G, 6D) are deflected fully downwards.

Abstract: A method of transferring and processing flight data of an aircraft including recording the aircraft flight data in an onboard avionics system in a digital format so as to obtain digital data, the flight data including safety impact flight data and flight data having no recognized effect on safety. The method further includes recording at least the safety impact flight data in the onboard avionics system in an additional format dissimilar to the digital format so as to obtain additional flight data, storing the digital data and the additional flight data separately, transferring the digital data and the additional flight data to a monitoring computer on the ground, displaying the digital data on a screen in the form of display digital data, and transferring the digital data and the additional flight data to a complementary interpretation unit so as to generate one of display data and print data relating to the additional flight data.

Abstract: A method of characterizing and counting violations of a threshold by an operating parameter of an aircraft engine of an aircraft includes detecting, by the aircraft, a violation of the threshold by the operating parameter while the aircraft engine is in operation. The method also includes, on detecting the violation, automatically transmitting from the aircraft to a ground system a warning message about the violation. Further, the method includes, on the basis of the warning message, automatically determining a severity level for the violation. In addition, the method includes incrementing a counter representing a number of occasions the operating parameter of the aircraft engine has presented a violation corresponding to the severity level.

Abstract: A computer-implemented flight data monitoring method is provided for monitoring flight data, for example flight data obtained by a flight data recorder or quick access recorder on an aircraft. The method comprises receiving input flight data, performing flight data validation on the input flight data to generate validated flight data, and performing flight data analysis on the validated flight data to detect at least one predetermined type of flight event. The events may be useful for generating an aircraft safety report, for example. By validating the data before performing the analysis, the number of events which are falsely detected based on invalid or unreliable data can be reduced.

Abstract: Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.

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 method for rendering symbology on a cockpit display of a host aircraft, relating to a proposed ITP transition, is provided. The method comprises analyzing data to predict an ITP transition that is possible and economical, rendering on the display symbology textually representative of the possible ITP transition, and rendering on the display symbology textually representative of the time before which the ITP transition is possible.

Abstract: A display system and method for an aircraft renders various airspaces and associated airspace types on an aircraft display device. An image is selectively rendering on the aircraft display device that includes at least an airspace boundary graphic representative of at least a portion of the boundary for the airspace, and a textual airspace type designation label representative of the airspace type of the airspace.

Abstract: A system for facilitating autonomous landing of aerial vehicles on a surface. A beam emitter is directed downwards. A control module is configured to govern the vehicle. A processor processes image data. The beam emitter is arranged to emit simultaneously at least four beams directed towards the surface in order to project a pattern thereon. One beam emitter of the at least four beam emitters is placed in the center. An image capturing module captures subsequent images of the pattern.

Abstract: An electronic lead/lag damper algorithm implemented as part of the fly-by-wire flight control system to minimize or eliminate mechanical lead/lag dampers of a rotary wing aircraft. The electronic lead/lag damper algorithm uses a cross-feed control methodology that band-pass filters pitch and roll rates and feeds back a signal to the lateral and longitudinal cyclic inputs to provide electronic stability to rotor lag modes.

Abstract: The invention relates to systems and methods for displaying flight information representative of a deviation from a specified four-dimensional flight path. Particularly, but not exclusively, the invention relates to a cockpit display for enabling pilots to arrive at a particular location at a particular time and to achieve the necessary changes to aircraft speed to achieve a preferred ground speed. There is described a system and a method that displays flight information relating to a predetermined flight path. The predetermined flight path specifies locations and corresponding scheduled times. A current location of an aircraft along the predetermined flight path is monitored. A current time at which the aircraft is at the current location is determined. A scheduled time for the aircraft to be at the current location is provided. A time deviation between the current time and the scheduled time is calculated. The time deviation is displayed.

Abstract: The invention consists in merging together the predicted and measured meteorological data to supply them to the flight prediction calculation system so as to smooth the discontinuities brought about in the prior art by the simple update which is carried out. This merging is advantageously done by linear weighting of the data, the weighting coefficient depending upon the positioning in vertical and horizontal distances between the predicted point and the aeroplane in relation to chosen thresholds.

Abstract: A system for providing information to at least one passenger onboard a mobile platform (such as a train, marine vessel, aircraft or automobile) is provided. The system includes a display device that displays the information. The system also includes a source of user input coupled to the display device that enables the at least one passenger to request the information. The information includes at least galley information. The system further includes a galley control module that generates galley data that includes at least one food service item available onboard the mobile platform, and a graphical user interface module that displays the at least one food service item available onboard the mobile platform to enable the at least one passenger to select at least one of the at least one food service item.

Abstract: Embodiments of the present invention relate to a system and method for better conveying information to a pilot and/or other members of a flight crew present on the flight deck of an aircraft. Embodiments of the invention are of particular use in the briefings that precede various phases of the flight operations of an aircraft (such as start-up of the engines, take-off, ascent to cruise altitude, descent from cruise altitude and landing). The system and method provide a briefing output relevant to the particular phases of a flight in both of a visual form and an audio form, with the briefing output including data of most relevance to the particular flight phase.

Abstract: This aircraft control cabin comprises an avionics display device with multiple fixed screens (10a-10d) and at least one screen (15, 16) as an accessory, designed to be a replacement screen or extra screen for the avionics display system. The screen (15, 16) is a touch screen housed in a retractable tablet which slides underneath an instrument panel in the control cabin, the touch screen (15, 16) being designed to occupy a stowed position underneath the instrument panel, a first position of use in the retractable tablet in which the touch screen (15, 16) acts as a means of interaction for controlling various items in the control cabin and a second position of use in which the touch screen (15, 16) is put in a position in which it replaces or supplements a screen (10a-10d) belonging to the avionics display system. Use in an aircraft.

Abstract: Methods and apparatus are provided for transmitting incursion alerts to a plurality of in-flight aircraft in accordance with preconfigured pilot preferences. The apparatus comprises a data store module containing data sets against which the pilot preferences are evaluated during flight, including weather, airspace and flight restrictions, ground delay programs, and air traffic information. The apparatus further includes a flight path module containing route and position information for each aircraft. An incursion alert processing module evaluates the flight path, data store, and pilot preferences and generates incursion alerts which are transmitted to each aircraft during flight, either directly or via ground based dispatchers or flight operations personnel.

Abstract: Systems and methods for providing aircraft heading information are provided. In one embodiment, an attitude heading reference device comprises: at least one interface for receiving heading information from one or more IRUs; at least one set of gyroscopes and accelerometers; a memory device for storing data representing heading information received via the at least one interface; and a heading calculator coupled to the at least one interface, the at least one set of gyroscopes and accelerometers, and the memory device. The heading calculator generating a heading output signal based on heading information when reliable heading information is received over the at least one interface; the heading calculator generating the heading output signal based on data from the memory device regarding previously reliable heading information and an output of the at least one set of gyroscopes and accelerometers when reliable heading information is not received over the at least one interface.

Abstract: The display device (1) comprises means (3) for correcting an acceleration value used for displaying on a screen (7) a speed trend of the airplane, making it possible to zero a speed trend symbol (11) when the Mach number of the airplane does not vary.

Abstract: Systems and methods for providing aircraft heading information are provided. In one embodiment, an attitude heading reference device comprises: at least one interface for receiving heading information from one or more IRUs; at least one set of gyroscopes and accelerometers; a memory device for storing data representing heading information received via the at least one interface; and a heading calculator coupled to the at least one interface, the at least one set of gyroscopes and accelerometers, and the memory device. The heading calculator generating a heading output signal based on heading information when reliable heading information is received over the at least one interface; the heading calculator generating the heading output signal based on data from the memory device regarding previously reliable heading information and an output of the at least one set of gyroscopes and accelerometers when reliable heading information is not received over the at least one interface.

Abstract: A sling load computer-operated hook assembly for helicopter or unmanned aerial vehicle (UAV) use is provided. The hook assembly allows automated pick-up and delivery. The computer hook assembly also (1) directs navigation of the aircraft, (2) finds and engages loads for pickup, (3) controls stability of the sling load enroute, and (4) releases the load at the delivery point. The self-contained feature allows the hook assembly to be moved from aircraft to aircraft. The hook assembly senses weight, motion and position of the load for stability control. An integral GPS unit is used to direct navigation. These data are transmitted to the aircraft autopilot and flight director instruments to provide navigation to the designated points and to control load stability enroute. Mission data for pick-up and release points can be received remotely from a command and control tactical data net. Alternately, mission data can be locally entered.

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 centred 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 centred 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.