Abstract: A method of determining a maneuver performed by an aircraft having sensors for monitoring motion data, the method including periodically sampling the sensors to electronically determine segments of motion data of the aircraft; aggregating sequences of the segments of the motion data; comparing the aggregated segments of motion data to models of particular maneuvers; and determining the maneuver performed by the aircraft.

Abstract: A method and apparatus for managing separation between vehicles. A closest point of approach between a first vehicle traveling along a first path and a second vehicle traveling along a second path is predicted. A number of compensation commands for altering the first path of the first vehicle are generated using the closest point of approach and a desired level of separation between the first vehicle and the second vehicle. The number of compensation commands is integrated with a number of control commands for the first vehicle to form a final number of control commands configured to maneuver the first vehicle to substantially maintain the desired level of separation between the first vehicle and the second vehicle. A response of the first vehicle to the final number of control commands is a desired response.

Abstract: The invention relates to a process and an on-board system for evaluating flight strategies aboard an aircraft, linked with a flight plan (13) of the aircraft, including: calculation means (5) for determining relations between the flight parameters including parameters of time, of fuel quantity, of altitude and of speed, interface means (9) for providing at least one envelope of values (25a-25d) representative of a domain of definition of a plurality of flight strategies, interface means (9) for providing at least one determined strategy defined by determined values assumed by the flight parameters at a reference point, interface means (9) to allow the selection and setting of the value of a first parameter among said flight parameters, generating and supplying another envelope of values allowing exploration of another plurality of possible strategies, and interface means (9) to allow the selection and setting of the value of a second parameter, generating and supplying another determined strategy.

Abstract: A system including a switching device for switching an auxiliary display unit between a first state, corresponding to nominal operation, for which a screen of said auxiliary display unit is controlled by a control assembly of a main display unit, and a second, standby state, corresponding to a situation in which the main display unit has broken down, for which state said screen is controlled by a control assembly of said auxiliary display unit.

Abstract: Systems and methods for aircraft cabin noise analysis are disclosed. In one embodiment, a computer based system to monitor vehicle conditions comprises a trigger table stored in a tangible computer readable memory which stores at least one set of logic conditions which may trigger directive to analyze if alert conditions exist. The system further comprises a trigger processor to receive one or more data streams comprising vehicle condition data for a monitored vehicle and transmit the directive to analyze alert logic to an alert evaluation queue when the vehicle condition data satisfies the at least one set of logic conditions in the trigger table, and an alert evaluation processor to execute a stand-alone program to analyze vehicle data and generate an alert when the vehicle condition data satisfies the at least one set of alert conditions. In some embodiments, the system may be implemented in a computing system or as logic instructions recorded on a computer readable medium.

Abstract: An electronic flight bag apparatus includes an electronic flight bag (EFB) system installed in an aircraft and which interfaces with a ground network, and a portable EFB device connectible with the EFB system via a trusted secure connection. This apparatus makes it possible for a flight crew member to remove the portable device from the aircraft, enter flight information into the device in a convenient manner, and transfer the information to the installed EFB system. Auxiliary crew members may use the portable device during flight to assist the flight crew.

Abstract: Systems and methods for providing vehicle-centric collision avoidance are disclosed. An example method includes determining a first flight trajectory for a first aircraft, determining a second flight trajectory for a second aircraft, determining a predicted first distance between the first aircraft and the second aircraft at a first closest point of approach based on the first and second flight trajectories, comparing the predicted first distance to a first separation perimeter layer, the first separation perimeter layer defining a first three-dimensional perimeter based on the first aircraft, determining a first adjustment having a first magnitude from the first flight trajectory when the predicted first distance is within a first perimeter, determining a second adjustment having a second magnitude from the first flight trajectory when the predicted first distance is within a second perimeter different from the first perimeter, and altering the first flight trajectory based on the first or second adjustment.

Abstract: The present invention comprises methods and apparatuses for sensing attributes of an aircraft and efficiently communicating relevant attributes to a pilot. The invention allows a state of the aircraft to be determined, and then used to control systems, configure displays, select checklists relevant to the determined state, and automatically respond to emergencies based on the aircraft state. Embodiments of the invention can use the determined state of the aircraft to monitor and control electrical sensors and system as appropriate for the determined state; to communication information relevant to the determined state to a pilot (e.g., by displaying gauges in a manner and priority specific to the determined state); and to display contextually-relevant checklists (e.g., displaying a checklist of actions necessary for an aircraft in the determined state).

Abstract: A monitoring device is disclosed for an actuation system of an aircraft for monitoring a guiding device of a regulating flap with a load sensor. An actuation system with the monitoring device and a method for reconfiguring such an actuation system are disclosed. The monitoring device includes an interface to the load sensor and an interface to a driving device for adjusting the regulating flap. The monitoring device can determine or receive in-flight information actively signaling a predefined flight attitude and/or a predefined operational state of the aircraft. The monitoring device can compare a load value corresponding to a sensor value acquired by the load sensor and a limiting value corresponding to a minimum operational load for the predefined flight attitude and/or the predefined operational state of the aircraft and a monitoring function. The monitoring function can assign a fault mode to the regulating flap.

Abstract: A system for providing sideslip envelope protection includes a processor for obtaining values of a sideslip envelope indicative of operating conditions of the aircraft along an axis and for estimating a sideslip angle along the axis from at least one operating condition; and a comparer for comparing the sideslip angle with the sideslip envelope to generate an output value, where the processor determines a maximum yaw rate from the output value and scales the maximum yaw rate to generate a scaled yaw rate.

Abstract: A computer implemented method, apparatus, and computer usable program product for cross checking required navigation performance procedures. A required navigation performance procedure in a flight management system is executed in an aircraft. A global positioning system signal in an electronic flight bag or other independent data processing system located onboard the aircraft is received while executing the required navigation performance procedure. A current position of the aircraft based on the global positioning system signal is presented on a moving map. A set of containment lines on the moving map are displayed to indicate whether deviations from the required navigation performance procedure have occurred.

Abstract: A method and apparatus for displaying aircraft performance characteristics. A two-dimensional representation of a flight envelope for an aircraft is displayed. The two-dimensional representation of the flight envelope comprises a display of speed versus altitude performance capabilities of the aircraft. A current speed and a current altitude of the aircraft are identified. A performance indication of the current speed and the current altitude is displayed on the two-dimensional representation of the flight envelope. A position of the performance indication on the two-dimensional representation of the flight envelope indicates the current speed and the current altitude with respect to the flight envelope.

Abstract: A method and apparatus for simulating effects of threats to aircraft communications. A simulation of an aircraft environment is run with the aircraft communications in an aircraft communications network in the aircraft environment. A number of conditions is introduced. The number of conditions comprises a threat configured to affect the aircraft communications in the aircraft communications network in an undesired manner. A change in traffic flow of aircraft in an airspace in the aircraft environment is identified in response to the number of conditions.

Abstract: This device for displaying information relative to a flight configuration of the aircraft provided with at least one propulsion system, able to generate a thrust force on said aircraft comprised in a thrust range, said information comprising information relative to an energy variation of the aircraft, is characterized in that the energy variation of the aircraft is expressed by a size representative of this energy variation and homogenous at a gradient of the aircraft, and in that said device is capable of representing a range of energy variations that can be achieved by said aircraft and a current energy variation of said aircraft. Corresponding method and system for displaying an energy variation.

Abstract: Systems and methods to manage aircraft dispatch information are provided. A particular method includes receiving fault information at a dispatch information computing system. The fault information is associated with an aircraft. The method also includes accessing operational restriction information associated with the aircraft based on the fault information. The method further includes automatically determining a set of bottom line operational limitations of the aircraft based on the fault information and the operational restriction information. The method also includes generating customized checklists for the various users of the information. The method also includes sending output data from the dispatch information computing system to an output device. The output data identifies the set of bottom line operational limitations of the aircraft and tasks to be completed by the various users.

Abstract: Embodiments of the invention provides an automatic deployable flight recorder (ADFR) system that includes a deployable fight recorder, a plurality of crash sensors, and a recorder release unit. The recorder release unit is communicatively coupled to the deployable fight recorder and the plurality of crash sensors, and is configured to initiate deployment of the deployable flight data recorder from an aircraft when a deployment criteria that is adjusted based on a flight condition of the aircraft is satisfied.

Abstract: A system and method of providing aerial navigation for an aircraft comprises presenting an enlarged virtual runway for an identified runway on a display, where the virtual area of the virtual runway remains substantially constant as the aircraft approaches the runway.

Abstract: A system and method for analyzing a risk of extended operations (ETOPS) dual independent engine in-flight shutdown (IFSD) using an ETOPS IFSD risk calculation means is disclosed. A two-engine aircraft/engine combination performance data set is provided to obtain flight specific data, and a user input variable array is also provided. Flight times are calculated based on the flight specific data and the user input variable array. Dual independent engine shutdown total thrust loss probability values for various phases of an ETOPS flight are calculated based on the user input variable array, the flight specific data, and the flight times. A calculated risk of dual independent engine in-flight shutdown on the ETOPS flight is calculated based on a sum of the dual independent engine shutdown total thrust loss probability values.

Abstract: A method of an aircraft communicating a current position status, a current movement status, a current intent, and/or an intended future path, position, or intent of the aircraft may include the aircraft generating explicit first ownship information related to the current position status and/or the current movement status, or current intent of the aircraft, and/or a flight management or other aircraft system of the aircraft generating information related to the intended future path, position, or intent of the aircraft. The aircraft may transmit the explicit first ownship information and/or the second information using an automatic dependent surveillance broadcast system transmitter. An airborne and/or ground receiver may receive the transmitted information related to the explicit first ownship information and/or the second information.

Abstract: The different advantageous embodiments provide a method for generating an integrated aircraft clearance. Flight information, preference information, environmental information, and constraints are retrieved from a number of sources. The flight information includes at least one of flight plan information, flight scheduling information, flight status information, and environmental information. The flight information is processed against the preference information, the environmental information, and the constraints. A clearance solution is generated for an aircraft based on the flight information, the preference information, the environmental information and the constraints.

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 vision system for an aircraft according to the invention comprises a display management system, on a display, capable of dynamically displaying synthetic information coming from a synthetic environment generating assembly on the display. The management assembly can control the display, on a first region of the display, of relief lines representative of the terrain situated facing the aircraft, without displaying synthetic surface representations of the terrain in the intermediate areas situated between the relief lines of the first region of the display. The generating assembly includes means for determining the position of the crest lines of the terrain from topographical data present in at least one database, and means for computing the position of the relief lines from the position of the crest lines of the terrain.

Abstract: The display device comprises display means which highlight on a screen, preferably of PFD type, the information useful to the pilot relating to at least one flight parameter, especially while reducing the corresponding scale on said screen.

Abstract: Methods and systems for managing maintenance of a fleet of aircraft are provided. The method includes collecting data from at least one aircraft in each of the fleets related to the operation of the aircraft, determining a range of acceptable values of performance parameters associated with the collected data and based on the collected data, analyzing the collected data having values outside the range of acceptable values, and modifying at least one of a maintenance requirement and an interval between maintenance actions to facilitate reducing the number of performance parameters values that are outside the range of acceptable values during future operation of the aircraft.

Abstract: Methods, systems, and apparatus for tab-pane-based flight plan management interface are disclosed. The tab-pane-based flight management interface system (FMIS) is optimally Layered and Multi-Indexed (LMI) such that the management of flight management (FM) functions and associated parameters that affect the airplane's flight are easily and efficiently operable by pilots. The LMI-FMIS provides a flexible tab-pane-based architecture that allows pilots to start a flight plan modification, proceed to engage in other tasks not related to the modification, and return to the pending modification to continue the modification process. The LMI-FMIS also provides task-oriented menu structures that provide pilots tailored options or menus applicable to the task at hand thus efficiently guiding pilots to complete a task while maintaining easy access to information that was displayed prior to the commencement of the task.

Abstract: A method and module for displaying a munition release envelope.

Abstract: The flight of an aircraft is characterized in terms of Earth-based reference system data for a first position and a second position of the aircraft that are separated by a time increment. A centripetal acceleration of the aircraft is determined based on the Earth-based reference system data for the positions in conjunction with the time increment. A rate of rotation is established corresponding to the time increment in an aircraft-based reference system. Aircraft airspeed is determined based on the centripetal acceleration and the rate of rotation. A turn can be detected as characterized by a change in track angle from a prior GPS packet compared to a new packet. Aircraft turns can be detected based on a change in track angle in GPS packets. Compensation can be applied to a gyro based on centripetal acceleration such that the gyro more accurately responds to the Earth gravity axis.

Abstract: A method of controlling a high-speed rotary wing aircraft (1) comprising a fuselage (2), at least one main rotor (3), at least one variable-pitch propulsive propeller (4), at least two half-wings (11, 11?) positioned on either side of said fuselage (2), at least one horizontal stabilizer (20) provided with a movable surface (21, 21?), and at least one power plant driving said main rotor (3) and said propulsive propeller (4) in rotation. Said method serves to adjust the lift of said half-wings (11, 11?) and the lift of the horizontal stabilizer (20) so that said lift of said half-wings (11, 11?) represents a predetermined percentage of the total lift of said aircraft (1) and so that the power consumed by said main rotor (3) is equal to a setpoint power during a stage of stabilized flight.

Abstract: A method of controlling a high speed rotary wing aircraft (1) comprising: a fuselage (2); at least one main rotor (3); at least one variable pitch propulsive propeller (4); at least two half-wings (11, 11?) positioned on either side of said fuselage (2); at least one horizontal stabilizer (20) provided with a movable surface (21, 21?); and at least one power plant driving said main rotor (3) and each propulsive propeller (4) in rotation. Said method serves to adjust the lift of said half-wings (11, 11?) and the lift of the horizontal stabilizer (20) so that the collective pitch of said blades (31) of said main rotor (3) is equal to a setpoint collective pitch, so that the longitudinal cyclic pitch of said blades (31) of said main rotor (3) is equal to a setpoint longitudinal cyclic pitch, and so that the lateral cyclic pitch of said blades (31) of said main rotor (3) is equal to a setpoint lateral cyclic pitch during a stabilized stage of flight.

Abstract: A method, computer system, and computer program product for displaying flight information. A number of elements for a number of phases of flight for a route of an aircraft are identified. The number of elements in association with the number of phases of flight is displayed on a strip on a display. The number of elements is displayed on the strip in a sequence in which the number of elements is encountered by the aircraft on the route during the number of phases of flight.

Abstract: A method and device for precise control of and controller design for aircrafts consisting of at least one spinning part and at least one non-spinning part is provided. The required torques for control of the spinning parts and for the non-spinning parts are continuously and individually calculated. All torques are combined to get the correct torque for the complete aircraft. Doing this, it's possible to continuously apply the correct torque, both correctly distributed among the roll and pitch axes (correct angle), and correct magnitude. The result is a decoupling of the roll and pitch axes, simplifying controller design to a design of two single input single output controllers, one for each axe.

Abstract: A system to monitor aircraft equipment, having a chassis, defining an interior compartment, an arrangement configured to accept input data of at least one aircraft parameter, the arrangement configured to be placed within an aircraft, crash survivable cockpit voice and flight data recorder, and a power supply arrangement connected to arrangement configured to accept input data and the recorder.

Abstract: Disclosed are a method and system for improving real-time determination of flight parameters of an aircraft during flight. A selection module selects and delivers measured values of input parameters to an estimation unit, and the estimation unit uses the input parameters to estimate at least two selected flight parameters. The input parameters are received by the estimation unit on the basis of identified flight mechanics equations associated with the selected flight parameters. The estimation unit includes an extended Kalman filter, which is configured to receive the values of the input parameters and to output joint estimations of the selected flight parameters based on the flight mechanics equations, during the flight of the aircraft.

Abstract: A 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. An electronic system comprising a receiver module and a mobile device, whereby the receiver module is capable of receiving data transmissions from a network of ground stations and buffering the data for future use.

Abstract: Novel diagnostic methods for performance of a launch vehicle are disclosed. A method may include computing energy for a pre-flight trajectory of a vehicle using angular momentum of the vehicle, and comparing a difference in energy between the energy for the pre-flight trajectory of the vehicle and energy for a flight trajectory of the vehicle.

Abstract: A taxi method for an aircraft having a primary thrust engine taxi system and an electric taxi system is provided. The method involves obtaining aircraft and airport status data and generating therefrom taxi drive information indicative of the relative cost of taxiing the aircraft along a predetermined route using the electric taxi system versus the aircraft engine taxi system. The taxi drive index information is presented to a user.

Abstract: The display system (1) comprises means (5, 11A, 14) to take into account a recorded symbology, in the event of a malfunction in the emission of a symbology, to perform a display of symbology.

Abstract: A method of determining a turbulent condition in an aircraft with a handheld device where the handheld device has at least one of a gyroscope, seismometer, and an accelerometer where the method includes receiving an output from the at least one of the gyroscope, seismometer, and accelerometer while the handheld device is located within the aircraft and providing an indication of a turbulent condition.

Abstract: Touch or proximity sensors are integrated into control devices such as knobs, dials or wheels incorporated in a user control panel. A control output processor detects whether any of the sensors are outputting signals indicating that a control device is being touched (or nearly touched) by a user. The control output processor causes an associated display area to be highlighted or otherwise modified on a display screen to indicate to the user which control device is being touched. This feature allows for “no-look” interaction with control panels, and keeps the user's eyes focused on the relevant displays where the control devices produce effects. This allows users to preview and verify that the correct control device is being manipulated prior to taking any (potentially erroneous) control actions.

Abstract: An aviation yoke HSI interface and flight deck control indicator and selector safety system enhances flight safety. The system incorporates a multi-controlled HSI with a yoke heading adjustment control, a yoke radial/course selector, and a yoke heading centering control positioned on a yoke, stick, or collective. The system may also incorporate a first officer multi-controlled HSI with a first officer yoke heading adjustment control, a first officer yoke radial/course selector, and a first officer yoke heading and course centering control. An autopilot mode indicator visually indicates whether an autopilot is flying according to a desired heading or according to a navigational aid signal, such as a VOR radial signal. A side selector-indicator control permits selection of which side controls the flight of the aircraft.

Abstract: A flight management system is provided for generating a variable thrust cutback during aircraft departure. The flight management system includes memory storing a sound exposure level limit for a navigation flight and storing expected sound exposure levels for an aircraft, and one or more inputs for receiving sensed aircraft variables including altitude and airspeed. The system also includes a processor for processing the sensed altitude and airspeed and stored sound exposure levels. The processor further computes an engine thrust value that complies with the sound exposure level limit based on the altitude, airspeed and the sound exposure levels for controlling aircraft throttle during departure.

Abstract: An apparatus for holding a flight data recorder in an aircraft includes a housing that defines a compartment enclosing the flight data recorder and a flotation device encapsulating the flight data recorder. If the aircraft crashes into a body of water and become submerged, one or more releasable fasteners holding the compartment's cover in place are triggered thereby removing the cover over an opening in the compartment and ejecting the flotation device and the flight data recorder out of the compartment. The floatation device then floats the flight data recorder to the surface of the water where it can be located by the rescuers.

Abstract: Systems and methods are operable to present graphical information indicating capability of an aircraft to change altitude. An exemplary embodiment determines an altitude change capability of the aircraft; determines an altitude change capability icon based on the determined altitude change capability of the aircraft, wherein the altitude change capability icon is defined by at least a leading portion, a trailing portion, a top portion, and a bottom portion, wherein a slope of the leading portion of the altitude change capability icon corresponds to the determined altitude change capability of the aircraft, and wherein the leading portion and the trailing portion are separated by at least the top portion and the bottom portion; and communicates the altitude change capability icon to a display for presentation to the crew of the aircraft.

Abstract: A method for health monitoring for an aircraft includes the steps of obtaining vibration data for the aircraft, obtaining navigation data for the aircraft, and determining a measure of health of the aircraft using the vibration data and the navigation data.

Abstract: A system is provided for controlling the speed of an aircraft with a speed brake during flight. The system includes a guidance system configured to determine a target speed for the aircraft; a speed brake control system coupled to the guidance system and configured to compare the target speed to a current speed to generate speed brake guidance; and a display unit coupled to the speed brake control system and configured to display a visual representation of the speed brake guidance to a pilot of the aircraft.

Abstract: A system for displaying pitch- and power-based guidance commands and flight path information for a variety of display modes (climb, cruise, descent, landing) to pilots in response to situations wherein the measured air data should not be relied upon. This information is presented in an intuitive and expedient manner exactly when and where it is needed on the primary flight display. The displayed information dynamically changes in response to airplane parameters.

Abstract: Onboard systems and methods for detection of airborne volcanic ash. One or more cameras are added to an aircraft. Each camera is configured to view a volume of air illuminated by a standard aircraft light, such as a strobe warning light (e.g., located on a wing tip) or a forward-facing landing light (e.g., located in the nose). Each camera is connected to a data processor. When diffuse volcanic ash is present, it scatters light transmitted from the standard aircraft light. Each camera converts impinging backscattered light into digital data which is sent to the processor. The processor processes the data from the camera or cameras to derive a measurement of the backscattered light and issues an alert when the amount and type of backscatter are compatible with the presence of volcanic ash.

Abstract: The invention relates to an aircraft control system containing several aircraft control computers (14, 16, 18, 20) for said aircraft, said system having at least one server (10) which: contains at least one aeronautical data base (12); is connected to at least one subassembly of said control computers through data transmission links (26a, 26b, 26c, 26d); is able to supply information from said at least one aeronautical data base to the computers of said control computer subassembly, said at least one server being able to supply information from said at least one aeronautical data base to a computer of said control computer subassembly, in a period of time less than a predetermined duration, upon request from said computer, when said information is not available in a local data base of said computer.

Abstract: According to one embodiment, an aircraft part environmental stress analysis system includes a part failure repository, a part history repository, and a failure analysis engine. The part failure repository is configured to store a plurality of failure records, each failure record identifying a failed aircraft part. The part history repository is configured to store a plurality of part records, each part record storing, for a failed aircraft part, at least one measurement of an aspect of a natural environment of which the failed aircraft part was subject to. The failure analysis engine is operable to compare the plurality of failure records to the plurality of part records and identify at least one potential environmental cause of failure for a plurality of failed aircraft parts based on the comparison.

Abstract: According to an embodiment, a method provides flight operational consequence information by receiving a status indication associated with an aircraft component at a processing device in the aircraft during a flight. The processing device ascertains one or more operational consequences that includes displaying text strings associated with the status indication, wherein each of the one or more operational consequences are associated with one or more flight segments of the flight. At least a subset of the one or more operational consequences are provided on a display associated with the processing devices and an indication is provided on the display of the one or more flight segments associated with the one or more operational consequences.