Abstract: Disclosed are algorithms and agent-based structures for a system and technique for analyzing and managing the airspace. The technique includes managing bulk properties of large numbers of heterogeneous multidimensional aircraft trajectories in an airspace, for the purpose of maintaining or increasing system safety, and to identify possible phase transition structures to predict when an airspace will approach the limits of its capacity. The paths of the multidimensional aircraft trajectories are continuously recalculated in the presence of changing conditions (traffic, exclusionary airspace, weather, for example) while optimizing performance measures and performing trajectory conflict detection and resolution. Such trajectories are represented as extended objects endowed with pseudo-potential, maintaining objectives for time, acceleration limits, and fuel-efficient paths by bending just enough to accommodate separation.

Abstract: A flight data aggregation system for a plurality of aircraft includes one or more portable electronic devices in electronic communication with one or more central computers. The one or more portable electronic devices each monitor flight data from a corresponding aircraft. The one or more portable electronic devices analyze the flight data in real-time to determine an insight event indicating an incident of significance is presently occurring upon the corresponding aircraft. Each central computer includes one or more processors and a memory coupled to the one or more processors. The central computers are caused to receive the flight data collected during the insight event from an individual portable electronic device. The central computers determine overall flight data patterns based on the flight data collected during the insight event received from the individual portable electronic device and historical data stored in the one or more databases.

Abstract: A method for providing a visual driving speed recommendation to an operator of a vehicle includes determining a current speed; determining a corresponding energy efficient speed; determining a higher corresponding less energy efficient speed; determining a first transition range between the corresponding energy efficient speed and the higher corresponding less energy efficient speed; and displaying, on a display, a display zone, the display zone comprising: a first indicator corresponding to the current speed; a first pattern corresponding to the corresponding energy efficient speed; a second pattern different from the first pattern and corresponding to the higher corresponding less energy efficient speed; and a first pattern range therebetween corresponding to the first transition range.

Abstract: The invention relates to a system and method for navigating an autonomous driving vehicle (ADV) that utilizes ADV an-onboard computer and/or one or more ADV control system nodes in an ADV network platform. The on-board computer receives sensor data concerning one or more occupants occupying an ADV and/or the ADV itself and, upon a detection of an event, automatically initiates a dynamic routing algorithm that utilizes artificial intelligence to re-route the ADV to another destination, for example a healthcare facility. One or more embodiment of the system and method include an ADV on-board computer and/or one or more ADV network platform nodes that utilize in-memory processing to aid in the generation of routing, health and navigational information to advantageously navigate an ADV.

Abstract: Methods and systems for visualization of mobile terminal communication link status are disclosed. In some aspects, one or more mobile terminal icons are provided for display on a map of a geographic area at map locations representing geographic locations of the mobile terminals. Coverage area icons of one or more network services are also displayed on the map. Features of the mobile terminal and coverage area icons indicate a network status of the respective terminals and coverage areas. In some aspects, prior location icons representing prior locations of the mobile terminal(s) are displayed on the map. In some of these aspects, clicking or hovering on the prior location icons provides for display, link performance data when the corresponding mobile terminal was at the geographic location represented by the prior location icon.

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: A system and method are provided for graphically displaying airspace data including speed restrictions on an aircraft display. The system comprises an avionics display system coupled to a processor that is configured to retrieve airspace data from a database, display the aircraft data on the display, and display a visual representation of the airspace. Then the processor may alter the format of the visual representation of the airspace to a second visual representation, if the airspace data meets predetermined criteria.

Abstract: A method of presenting attitude and heading information of a vehicle on a display to a viewer inside the given vehicle, comprising the steps of: using a 2D display, using data provided by an inertial reference system, using a computer and graphical software for treating the data and defining graphical elements, depicting the graphical elements in 3D on the 2D display, and presenting the attitude and heading information on the 2D display by associating them to at least one graphical element.

Abstract: A method and device establishes trajectory planning, predictions and guidance so as to obtain the satisfaction of a time constraint (RTA). This objective is achieved by undertaking a computation of a trajectory up to the point where the flypast time constraint applies, on the basis of a profile of altitude and speeds, and then by computing the profile of speeds and altitudes making it possible, throughout the computed trajectory, to comply with the RTA. The method is also a method for readapting the trajectory and the vertical profile when during a mission, the data outside the aeroplane have caused the time predictions to drift and the constraint is no longer complied with under the initial speeds and trajectory assumptions.

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: In some embodiments, a system is provided that includes a portable electronic device; and an application executable on the portable electronic device, the application including computer program code that (a) monitors acceleration data during a flight of an airplane; and (b) displays a representation of the acceleration data in relation to a threshold acceleration of the airplane. Numerous other aspects are provided.

Abstract: Systems and methods are provided for automated collection and analysis of aircraft flight data. In accordance with one aspect, a system for collecting flight data associated with an aircraft is provided to transmit collected flight data to a remote system for storage and processing. In accordance with another aspect, a remote system utilizes received aircraft location data to determine whether an aircraft flight incident has occurred, and to alert appropriate emergency services. In accordance with another aspect, a remote system analyzes received aircraft flight data and quantitatively evaluates performance of a pilot. In yet another aspect, a system is provided for graphical and textual display of collected aircraft flight data and pilot performance evaluation data.

Abstract: A method for presenting the current drift values of an aircraft on a display device in which the drift values are presented in a vector presentation. The length of the drift vector above a predefined threshold value is presented in a manner proportional to the current drift velocity, and the length of the drift vector below the threshold value is presented in a manner disproportionate to the current drift velocity. There is a continuous transition between the two ways of presentation at the threshold value.

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 device calculates a first air speed representing an estimated air speed during flight using measurements of static pressure and total pressure onboard the aircraft. The device includes a storage device for storing in memory, in case of detection of a ground taxiing of the aircraft, the most recently determined value of static pressure corrected from induced aerodynamic effects. As a result, a second air speed representing the estimated air speed during the ground taxiing may be calculated by implementing a correction and using the most recently determined value of static pressure when the ground taxiing of the aircraft is detected. A method for automatically estimating an air speed of an aircraft is also provided.

Abstract: The invention relates to a system and a method for calculating flight predictions of an aircraft in which an intermediate prediction horizon is defined between the flight phase and the leg. This horizon, that is called vertical section, is defined such that the limit conditions that are applicable to it, for example the target speed, target altitude, characteristic altitude and maximum end-of-section distance, are valid for the entire vertical section. Thus, it is not necessary, in calculations to check the compatibility of the flight parameters with the applicable constraints, to arbitrarily select the constraint that must be given priority. Furthermore, this intermediate level architecture allows for a greater modularity of the prediction management software and therefore a greater factorization of the developments and greater ease of maintenance.

Abstract: The invention relates to a system including two integrated electronics instruments mounted onboard an aircraft and communication links between the two integrated electronics instruments, each integrated electronics instrument including independent determination of flight parameters of the aircraft and display of either flight parameters or navigation parameters of the aircraft. The system also includes a selection module making it possible to choose, from the sensors of the two integrated electronics instruments, those retained for determining the flight parameters. Embodiments of the invention also relate to a method using the system described above. The method includes selecting from the two integrated electronics instruments the sensors retained for determination of the flight parameters according to their availability, and displaying the determined flight parameters on the display of any one or both of the integrated electronics.

Abstract: Disclosed is a method and device for assisting guidance of an aircraft. A flight management system is used to determine guidance instructions that include speed instructions having at least one flight time constraint to guide the aircraft to a check-point. An accuracy level for complying with the flight time constraint and at least one error level for at least one flight parameter are generated by an accuracy generating unit. An operating margin for at least one second parameter is determined from the determined accuracy and error levels, with the operating margin being representative of air speed criterion values of the aircraft. A range determining unit is used to determine whether the range of air speed criterion values is within an air speed envelope of the aircraft, and the speed instructions are modified when the range of air speed criterion values is not within the air speed envelope.

Abstract: The general field of the invention is, within the framework of the terrain anti-collision systems for aircraft, the presentation on the displays for aiding the piloting and the navigation of a simplified symbology suited to these critical situations. More precisely, the symbols comprise guidance indications in the depictions representing the horizontal and vertical situation indicators as well as speed instructions and altitude instructions, indications relating to the propulsion of the jets as well as guidance messages.

Abstract: Methods and systems for operating an avionics system are provided. A set of data that is representative of traffic advisory information is received. A visual indicator is displayed to a user based on the set of data that is representative of the traffic advisory information. The traffic advisory information may be received by a user through a receiver and manually entered into an interface for viewing. Alternatively, the avionics system may automatically generate the visual indicator based on the traffic advisory information.

Abstract: A method and a device for detecting a thrust dissymmetry of an aircraft during a landing are disclosed. The detection device (6) comprises means (7) for detecting, upon a landing, that at least one of the engine control levers occupies an intermediary position comprised between a position threshold and a maximum speed position, as well as at least another engine control lever occupies an idling position, and means (9, 13) for triggering a warning when a landing condition is validated and at least one of the control levers occupies said intermediary position, at least another control lever occupying said idling position.

Abstract: Embodiments for displaying first and second images to a pilot of an aircraft are presented. The embodiments include, but are not limited to, obtaining a first image signal and a second image signal, commanding a display unit to display a first image on a display screen corresponding to the first signal, and computing an image moving velocity of the first image. The method further comprises estimating an image flow velocity for the second image based on the second image signal and comparing the image moving velocity of the first image to the image flow velocity of the second image. After the comparison, the display unit is commanded to display the second image overlaid on the first image, and commanding the display unit to establish an intensity of the second image within a predefined range based upon the comparison.

Abstract: The present general inventive concept relates to a system of method having an electronic flight display that meets the FAR 23.1311(b) regulatory requirement for redundant backup instruments in the cockpit. The present general inventive concept also provides a system and method to detect failures, obstructions, or improper operation of the aircraft pitot pressure sensing system using a combination of dissimilar sensor data that is independent from each other, e.g., allocated from different sources and employed for different purposes on different displays, and displays information on an avionics display screen.

Abstract: Systems and methods are provided for automated collection and analysis of aircraft flight data. In accordance with one aspect, a system for collecting flight data associated with an aircraft is provided to transmit collected flight data to a remote system for storage and processing. In accordance with another aspect, a remote system utilizes received aircraft location data to determine whether an aircraft flight incident has occurred, and to alert appropriate emergency services. In accordance with another aspect, a remote system analyzes received aircraft flight data and quantitatively evaluates performance of a pilot. In yet another aspect, a system is provided for graphical and textual display of collected aircraft flight data and pilot performance evaluation data.

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: An inertial navigation system which includes a first control system and a second control system is described. The first control system is configured to estimate a vertical velocity based in part on received vertical acceleration data. The second control system is configured to receive the estimated vertical velocity from the first control system and determine a compensated vertical velocity utilizing the estimated vertical velocity and airspeed.

Abstract: The field of the invention is that of the display in map form of an operating zone of an aircraft on a screen, and more particularly a method of processing topographic data of this operating zone of an aircraft in real time, based on a calculation of radials (R) centred on a reference point (O) defining an angular segment of topographic data. According to the invention, the method includes a subdivision of the operating zone to be mapped into a plurality of angular segment sections, each forming an individual zone (3), and an assignment of a processing priority and a refresh frequency specific to each individual zone defined according to a criterion of operational interest of the element to the aircraft.

Abstract: A system and method are disclosed for computing a vehicle's motion in four dimensions (e.g., three spatial dimensions and time) and reliably predicting the vehicle's arrival time at a predetermined location, by providing a graphical display to an operator of the vehicle's progress that enables the operator to adjust the vehicle's movement and achieve the desired arrival time. Specifically, a system and method are disclosed for computing the movement of an aircraft in four dimensions, predicting its arrival time at a predetermined waypoint, and displaying (in a highly intuitive format) the aircraft's progress in achieving that desired arrival time. The pilot can then adjust the movement (e.g., speed) of the aircraft in accordance with the parameter(s) displayed, in order to achieve the desired arrival time. Thus, for example, numerous aircraft could be scheduled to arrive at a specific final approach waypoint at a predetermined rate (e.g.

Abstract: The invention relates to a system including two integrated electronics instruments mounted onboard an aircraft and communication links between the two integrated electronics instruments, each integrated electronics instrument including independent determination of flight parameters of the aircraft and display of either flight parameters or navigation parameters of the aircraft. The system also includes a selection module making it possible to choose, from the sensors of the two integrated electronics instruments, those retained for determining the flight parameters. Embodiments of the invention also relate to a method using the system described above. The method includes selecting from the two integrated electronics instruments the sensors retained for determination of the flight parameters according to their availability, and displaying the determined flight parameters on the display of any one or both of the integrated electronics.

Abstract: A method and a system for indicating a target idle running speed, a predicted core speed, a predicted time to running, current engine state or automation modes of an operating aircraft engine, and indicating that the current core speed of the aircraft engine is less than a target idle running speed or is abnormally decreasing towards a target idle running speed. The indicators may be visual or aural. The visual indicators may include graphical or numeric symbols indicating the target idle running speed, the direction of core speed change, the predicted core speed at some future time, or current engine state or automation mode.

Abstract: Method and system for analyzing and processing information on one or more aircraft flight paths, using a four-dimensional coordinate system including three Cartesian or equivalent coordinates (x, y, z) and a fourth coordinate ? that corresponds to a distance estimated along a reference flight path to a nearest reference path location corresponding to a present location of the aircraft. Use of the coordinate ?, rather than elapsed time t, avoids coupling of along-track error into aircraft altitude and reduces effects of errors on an aircraft landing site. Along-track, cross-track and/or altitude errors are estimated and compared with a permitted error bounding space surrounding the reference flight path.

Abstract: A flight instrument, having an electronic display, is configured to fit within a standard instrument mount and within an array of standard instrument mounts. The instrument has the ability to emulate any standard or other instrument. This instrument can share its installed optional sensors with other instances of itself that do not include the optional sensors by way of network interfaces. The instrument can contain emulation for all standard instruments and have a menu to select which to display.

Abstract: A system and method are disclosed for computing a vehicle's motion in four dimensions (e.g., three spatial dimensions and time) and reliably predicting the vehicle's arrival time at a predetermined location, by providing a graphical display to an operator of the vehicle's progress that enables the operator to adjust the vehicle's movement and achieve the desired arrival time. Specifically, a system and method are disclosed for computing the movement of an aircraft in four dimensions, predicting its arrival time at a predetermined waypoint, and displaying (in a highly intuitive format) the aircraft's progress in achieving that desired arrival time. The pilot can then adjust the movement (e.g., speed) of the aircraft in accordance with the parameter(s) displayed, in order to achieve the desired arrival time. Thus, for example, numerous aircraft could be scheduled to arrive at a specific final approach waypoint at a predetermined rate (e.g.

Abstract: The field of the invention is that of the display in map form of an operating zone of an aircraft on a screen, and more particularly a method of processing topographic data of this operating zone of an aircraft in real time, based on a calculation of radials (R) centred on a reference point (O) defining an angular segment of topographic data. According to the invention, the method includes a subdivision of the operating zone to be mapped into a plurality of angular segment sections, each forming an individual zone (3), and an assignment of a processing priority and a refresh frequency specific to each individual zone defined according to a criterion of operational interest of the element to the aircraft.

Abstract: Red, green and white colored lights are emitted from navigation orientation indicating light emitting devices mounted within a helicopter rotor blade near its tip. The light emissions from such devices are under control to respectively indicate passage of the rotor blade through limited arcuate portions of the travel path of the rotor blade end tip. Operational control over the light emitting devices is effected by data processing of outputs from air-speed responsive sensors on the blade end tip.

Abstract: A graphical display of a nonlinear scale emulating the view of a mechanical drum gauge. The nonlinear scale may be used for the display of aircraft flight data including airspeed, altitude, heading, and other aircraft data suitable for presentation on a nonlinear scale. The nonlinear scale may scroll to display current aircraft data.

Abstract: Apparatus and methods for enhancing the accuracy of height above ground measurements in which the registration error between successive images taken of the terrain over which an aircraft is flying is minimized, the earlier image having first been transformed according to measurements of the aircraft linear and angular velocities, the focal length and attitude of the image sensor, and an initial, coarse height estimate. By an iterative process, a more accurate height estimate is obtained.

Abstract: A method and apparatus is disclosed for displaying a dynamic parameter of an aircraft, the apparatus comprises a display unit receiving a display signal and displaying a scale that changes dynamically and non-linearly in accordance with a selected display algorithm, the display unit further displaying a pointer pointing to said scale in accordance with a reading of said dynamic parameter, thereby emphasizing a range of said reading of said dynamic parameter.

Abstract: A method for displaying flight information includes displaying a first characteristic sign illustrating a speed vector of an aircraft. The method also includes determining a first longitudinal margin of maneuver of the aircraft as a load factor, and displaying a second characteristic sign such that a position of the second characteristic sign relative to the first characteristic sign illustrates the first longitudinal margin of maneuver.

Abstract: A display system for an aircraft includes a central unit configured to determine a speed vector of the aircraft and to determine a longitudinal margin of maneuver of the aircraft. The longitudinal margin of maneuver is expressed as a load factor and is related to one of a pitch-up maneuver and a pitch-down maneuver. The display system also includes a display unit connected to the central unit. The display unit includes a display screen configured to display a first characteristic sign illustrating the speed vector and a second characteristic sign illustrating the longitudinal margin of maneuver.

Abstract: In an aircraft flight instrument display system having a display screen for displaying flight information, an airspeed indicator is displayed in a vertical tape format, and has a low speed range indicator with a low speed range identified on the airspeed indicator by highlighting the low speed range, and has at least a settable indicator within the low speed range indicating a critical airspeed. The low speed range indicator and the critical airspeed indicator are both set with only manual inputs.

Abstract: Method and indicator for displaying information showing the airspeed tolerance margins for an aircraft.

Abstract: A novel graphical display apparatus (and methods) for motor vehicles. The apparatus has a display coupled to an interior portion of a motor vehicle and facing a driver of the motor vehicle. The display is coupled to an output for identifying a revolution per minute (RPM) value of an engine of the motor vehicle. The display has a first graphical display portion of the display for outputting a current gear indication of a current gear. The current gear is one of a plurality of gears in the motor vehicle. A second graphical display portion of the display for outputting one or more indication(s) of a past gear is coupled to the first portion of the display. The past gear is one of the plurality of gears in the motor vehicle that is used before the current gear. A third graphical display portion is also coupled to the display. The third display portion outputs an RPM value indication that corresponds to a current RPM value of the engine of the motor vehicle. The RPM value indication is coupled to the output.

Abstract: A system and methodology for determining the alertness of a driver of a motor vehicle including sensing at least one first movement characteristic of at least a first part of a motor vehicle, sensing at least one second movement characteristic of at least a second part of the motor vehicle, employing at least one time relationship between the at least one first movement characteristic and the at least one second movement characteristic in order to sense and to distinguish between driver initiated movements and non-driver initiated movements and determining the alertness of the driver of the motor vehicle based on at least one relationship between the driver initiated movements and the non-driver initiated movements.

Abstract: The device (1) comprises a first means (3) for measuring the effective value of the velocity vector of the aircraft, a computing unit (4) which determines a display value automatically and repetitively and which comprises a filtering means (6) which filters the value measured by the first means (3) so as to form a first term, a display unit (7) for presenting on a screen (2) a characteristic sign illustrating the velocity vector whose position on the screen (2) is representative of the display value, and a second means (9) for determining the derivative of a velocity vector controlled by an aircraft pilot. The computing unit (4) further comprises a computing means (10) which determines a second term from the derivative of the controlled velocity vector and a summator (12) which sums the first and second terms so as to form the display value.

Abstract: The present invention provides an alternative means of displaying aircraft flight information traditionally provided by a standalone rate of turn indicator on the aircraft instrumentation panel. The bank angle effective to achieve a rate of turn equal to a desired rate of turn for an aircraft is displayed to the pilot by generating and displaying one or more bank angle markers on the roll scale of an aircraft attitude indicator. The position of the desired rate of turn bank angle markers may be updated continuously as a function of airspeed and other flight parameters. The present invention enables a pilot to perform a coordinated turn at a desired rate of turn without having to reference a separate rate of turn indicator on the instrumentation panel and/or without having to independently calculate the associated bank angle according to any known “rule of thumb” or other estimation method.

Abstract: A human centered informational display is disclosed that can be used with vehicles (e.g. aircraft) and in other operational environments where rapid human centered comprehension of an operational environment is required. The informational display integrates all cockpit information into a single display in such a way that the pilot can clearly understand with a glance, his or her spatial orientation, flight performance, engine status and power management issues, radio aids, and the location of other air traffic, runways, weather, and terrain features. With OZ the information is presented as an integrated whole, the pilot instantaneously recognizes flight path deviations, and is instinctively drawn to the corrective maneuvers. Our laboratory studies indicate that OZ transfers to the pilot all of the integrated display information in less than 200 milliseconds. The reacquisition of scan can be accomplished just as quickly. Thus, the time constants for forming a mental model are near instantaneous.

Abstract: Terrain navigation apparatus (1) for a stationary or moving vehicle (2) when the apparatus (1) is mounted thereon, including a system (3) for determining position, velocity, altitude and attitude incorporating at least six sensing means operable to provide signals indicative of a first measured height (5), a first velocity (7) and a first position (9) of the vehicle (2), scanning means (11) operable to scan terrain (13) around the vehicle (2) and measure a range (15) from the vehicle (2) thereto, first combining means (17) for combining signals indicative of the first measured height, the range and the first position (5, 15, 9) of the vehicle (2), together with error estimates (19) associated therewith, and for outputting results of said combining process, error-estimating means (21) for receiving as input signals results of said combining process and for providing said error estimates(19), such that the error-estimating means (21) and first combining means (17) operatively interact to effect terrain navigati

Abstract: Indicator of a variable for an aircraft. The indicator (1A) according to the invention comprises means (13) for determining first and second target values respectively of a variable and of its derivative with respect to time, and display means (5, 6, 7) which depict on a display screen (7) a means of indication (14) of the first target value, which is arranged in such a way as to indicate this first target value on a graduated scale (8), and a means of indication (16B) of the second target value which is associated at least with an indicator element (11) indicating said derivative so that, when the latter points toward said means of indication (16B), said variable of the aircraft becomes equal to and remains equal to said first target value and said derivative is equal to said second target value.

Abstract: An aircraft instrument system that informs the pilot of whether, during the takeoff roll, the aircraft's acceleration rate is sufficient to ensure that V1 speed will be achieved at the expected time (and thus distance), and, if not, how far in distance the aircraft is lagging behind the required acceleration schedule.