Abstract: An aircraft system includes a visual display system; a printer; and a flight management system coupled to the visual display system and the printer. The flight management system includes a processor and a plurality of data sources coupled to the processor. The processor includes a crew interface module coupled to the plurality of data sources, a display driver coupled to the crew interface module and the visual display system, and a printer driver coupled to the crew interface module and the printer. The crew interface module is configured to generate a report from data from the data sources and to send the report to the visual display system via the display driver. The visual display system is configured to receive the report and to display the report.

Abstract: A system for detecting cursor interference includes a graphics engine configured to generate graphics information; a first evaluation unit coupled to the graphics engine and configured to evaluate the graphics information; a cursor generation unit coupled to the graphics engine and configured to generate cursor information, the cursor generator further configured to merge the cursor information and the graphics information into merged information; a second evaluation unit coupled to the cursor generation unit and configured to evaluate the merged information; and a display device coupled to the cursor generation unit and configured to display the merged information based on the evaluations of the graphics information and the merged information.

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 apparatus for detecting moving vehicles. A determination is made as to whether a number of vehicles are present in a video data stream received from a camera system. In response to the number of vehicles being present, a number of speed measurements for each vehicle in the number of vehicles are obtained from a radar system. A determination is made as to whether a speed of a set of vehicles in the number of vehicles exceeds a threshold. In response to a determination that the speed of the set of vehicles exceeds the threshold, a report is created for the set of the vehicles exceeding the threshold.

Abstract: Embodiments of the invention relate to a vehicle instrumentation systems and display systems employing multi-view displays in various land, water, air, and/or space vehicles. In one embodiment of the invention, an aircraft instrumentation system for a flight deck instrument panel includes at least one multi-view display configured to display at least two views, associating one view with a first crew member and the other view with a second crew member. In another embodiment of the invention, a standby instrument may be displayed on each of two multi-view displays such that a standby instrument is visible to each crew member at all times during aircraft operation.

Abstract: The method of optimizing the exit of an aircraft traversing for a known duration (D) a holding circuit forming a racecourse comprising two parallel branches of the same distance, the branches being traversed in a first time (t1), and two arcs of the same radius linking respectively the ends of each branch, the two arcs being traversed in a second time (t2), the holding circuit comprising an exit point situated at the end of one of the branches is characterized in that the distance of the branches of the holding circuit for the last two loops performed are adjusted so that the aircraft is substantially in proximity to the exit point when the duration (D) has elapsed.

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: A method displaying a pathway (226, 502) for an aircraft includes receiving (302, 402, 602) an instrument generated course generally in alignment with a runway centerline (214), determining (304, 404, 604) the pathway (226, 502) based on aircraft flight parameters in which the aircraft may fly in order to intersect the instrument generated course, rendering (306, 406, 606) on a display the instrument generated course and the pathway; and periodically repeating (308, 408, 608) the determining and rendering steps. The energy state of the aircraft may be considered in determining the pathway and optional indices (508) may be displayed indicating deviation from the pathway centerline.

Abstract: A device comprises means for computing the air-craft (A) current position, means for determining at least one maximum permitted deviation (E1) around a set position of the flight path of the flight plan according to accuracy and integrity performances of said current position computation and to the restriction of a flight range authorized in a flight corridor (6A, 6B), and a display system (7) for displaying at least one a distance scale (9) on a viewing screen (8), at least one a fixed symbol (10) displaying the current position and two movable pointers (13, 14) displaying the limits of said maximum permitted deviation (E1).

Abstract: An electronic display instrument configured to secure in a desired position over multiple pre-existing instrument holes in a dashboard of an aircraft in place of multiple conventional display instruments, each conventional instrument having a conventional readout. The instrument comprises a display screen having a plurality of readouts corresponding to the conventional readouts of the multiple conventional instruments that the electronic display instrument replaces. The instrument further includes a body having a front and a back opposite the front and a top and a bottom opposite the top. The body is positioned adjacent and connected to the display screen. The instrument also includes an electronics module protruding from the back of the body to position in one of the pre-existing instrument holes in the dashboard panel of the aircraft.

Abstract: The present disclosure is directed to a dynamic field of view (FOV) for a synthetic vision system (SVS) scene. The FOV within the SVS scene may switch between a FOV conformal to the real world outside of a vehicle and a wider FOV when beneficial. In an aircraft, for example, generating the SVS scene with the narrower FOV may be optimal during flight, while on the ground a wider FOV may improve situational awareness during taxiing. Determination of the airborne or grounded status of the aircraft may be based on speed, altitude, user input, or a received signal. Although the foregoing has been described within a particular context, the present disclosure is not limited to this scenario and may be applied to any vehicle in any situation where dynamically changing between a narrower FOV and a wider FOV is beneficial.

Abstract: A display system is provided that renders a horizontal situation indicator that includes required navigation performance (RNP) and estimated position uncertainty (EPU) values rendered non-numerically and in a fairly intuitive manner. A processor receives at least data representative of a desired course of the aircraft, data representative of the RNP for the aircraft, and data representative of the EPU for the aircraft. The processor renders, on a display device, a horizontal situation indicator that includes an aircraft symbol representative of a top-down view of the aircraft, an RNP boundary graphic representative of at least one RNP boundary for the aircraft, and an EPU graphic representative of the EPU for the aircraft.

Abstract: The invention pertains to optoelectronic devices for aiding the guidance and taxiing of aircraft, comprising a so-called head-up collimator allowing the presentation of information in the pilot's visual field. It applies notably to large-size civil aircraft of the Boeing 747 or Airbus A380 type. The optoelectronic device comprises means for calculating a deviation factor for the actual trajectory of said aircraft relative to a theoretical trajectory on said traffic way, means for generating symbols and at least one head-up collimator comprising means for displaying and superimposing said symbols on the outside landscape. The deviation factor is calculated on the basis of an angle (PÂ?G) and that the means for generating symbols generate a symbol representing said deviation factor, so as to be superimposed on said traffic way.

Abstract: The invention relates to aircraft instrument panel equipment. According to the invention, the proposal is for an instrument panel which, in addition to a main display system for horizon and necessary piloting parameters, comprises two items of equipment identical from the point of view of hardware and the point of view of software, each provided with a display screen, automatic pilot set point adjustment buttons, computing means and standby data (standby horizon, altitude, speed). In normal operating conditions, one of the items of equipment is configured in an “automatic pilot set point display” mode; its control buttons are used to give the set points to the automatic pilot computer, and the set points are displayed on the screen. The other item of equipment is configured in “integrated standby data display” mode. It displays on the screen the standby horizon, the standby speed and the standby altitude. The mode may be switched at will or in the event of a failure of one of the two items of equipment.

Abstract: Systems and methods for improving landing gear alerting on a rotary wing aircraft. An example system includes a user interface device that allows a user to set a bug altitude value and a radio altimeter that produces an altitude value, both of which are in communication with a processor. The processor receives a bug altitude setting, generates a landing gear alert altitude value based on the received bug altitude setting and a predefined additive, receives a radio altitude value for the rotary-wing aircraft, and generates a landing gear alert if the radio altitude value is less than the landing gear alert altitude value and the landing gear is not in a landing position. An output device in signal communication with the processor, outputs the generated landing gear alert.

Abstract: A display system and method for an aircraft displays, in real-time, the protected airspace associated with a CTL maneuver. The system processes aircraft approach category data and determines the protected airspace based at least in part on the processed aircraft approach category. An image representative of the determined protected airspace is displayed on the aircraft flight deck display system.

Abstract: A flight deck display system and related operating methods for an aircraft are provided. The system includes a processor architecture and a display element coupled to the processor architecture. The processor architecture is configured to receive real-time aircraft data and terrain data for the aircraft and, based upon the real-time aircraft data and the terrain data, generate image rendering display commands. The display element receives the image rendering display commands and, in response thereto, renders a primary flight display that includes a conformal view of terrain corresponding to a flight deck viewpoint. The primary flight display also includes a conformal terrain avoidance guidance (TAG) element on the view of terrain. The TAG element includes visual indicia of a desired navigation path that is intended to avoid terrain that obstructs a current flight path of the aircraft.

Abstract: The invention relates to a method and device for displaying a flight plan of an aircraft. The display device includes a display presenting unit making it possible to identify the flight phase of each waypoint of a flight plan which is displayed on a screen, and an activation unit making it possible to directly access a corresponding flight phase page.

Abstract: The parts of the flight plan of an aircraft corresponding to lateral trajectories at low altitude can comprise passages with limited lateral freedom of deployment because of risks of collision with the ground, or because of obstacles on the ground. The method makes it possible to signal them for the attention of the crew, so that said crew should redouble their attention. To do this it uses the display, on an onboard navigation screen, of a vertical profile of margin of maneuver relating to the navigation band widened to the right and to the left by lateral margins of maneuver, superimposed on the vertical navigation profile relating only to the navigation band.

Abstract: An interconnecting apparatus for interconnecting a pilot station of an aircraft to at least one aircraft zone includes a device for communicating between the pilot station and the aircraft zone. The aircraft zone includes a device permitting a person present in the aircraft zone to identify themselves and a display device indicating a functional status of the aircraft. The pilot station includes a display device indicating a location of each person being identified in the aircraft zone.

Abstract: Methods and apparatus are provided for enhancing the situational awareness of an operator. Automatic dependent surveillance-broadcast (ADS-B) traffic data transmitted by a traffic entity are received. The ADS-B traffic data are processed to determine traffic entity position. The traffic entity position is mapped to corresponding image coordinates on an enhanced vision system (EVS) display. A region of interest around at least a portion of the corresponding image coordinates is selected. An actual image of the traffic entity is rendered on the EVS display, at the corresponding image coordinates, and with at least a portion of the region of interest being highlighted.

Abstract: A method for displaying an operating parameter for a mobile platform. A plurality of different graphs can be digitized to place them in electronic form. Each graph represents a different operational or environmental characteristic relating to operation of the mobile platform, and each is further related to a common parameter. A first one of the digitized graphs is selected by a user. A user positionable marker is displayed on the first digitized graph at a specific, user selected location on the first digitized graph. Next a second one of the digitized graphs is selected. The second one of the digitized graphs is then overlayed over at least a portion of the first digitized graph, with the marker remaining visible and superimposed on the second digitized graph, and without having moved relative to the first digitized graph. The second digitized graph is then aligned relative to the first digitized graph. The marker is then used to assist in reading information from the second digitized graph.

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: Methods and systems for operating a display device are provided. A first image is caused to be displayed on the display device. The first image is at least representative of a field of view from on-board an aircraft. A second image is rendered over the first image on the display device. A luminance of at least a portion of the second image is temporally modulated.

Abstract: A navigation system for an aircraft, including a calculator of an estimated flight path for the aircraft; a device for determining an estimated value of a flight parameter that corresponds to an estimated speed for the extension of at least a portion of the high-lift devices of the aircraft; and a display of an indication for such estimated value. A command process for such a system and an aircraft equipped with such a system are also disclosed.

Abstract: A method and apparatus in a sensor network in an aircraft for collecting data about the aircraft. The sensor network in the aircraft collects the data about the aircraft. The sensor network comprises a set of wireless sensors attached to a first set of locations for the aircraft, a set of wireless routers attached to a second set of locations for the aircraft, and a set of gateways connected to an aircraft data processing system. The set of wireless routers is capable of receiving the data in wireless signals transmitted by the set of wireless sensors. The set of gateways is capable of receiving data in the wireless signals from the set of wireless routers to form received data and is capable of transmitting the received data into the aircraft data processing system.

Abstract: A reference value is arbitrarily selected from a range of possible aircraft rotation speeds. A position of a trimmable horizontal stabilizer is angled in accordance with a centering of the reference value. A deviation between the reference value and an accelerating speed value of the aircraft is determined. Elevators or the horizontal stabilizer are controlled, prior to rotation, in accordance with the determined deviation.

Abstract: A present novel and non-trivial system, module, and method for presenting an abbreviated pathway on a tactical display unit. A processor generates an image data set representative of a pathway and a three-dimensional perspective scene outside the aircraft using terrain data, first location highlighter data, and second location highlighter data, where the first location highlighter data corresponds to the active flight path and second location highlighter data corresponds to a subsequent flight path. After being presented to a display system, an image represented in the image data set is presented on a tactical display unit, whereby an abbreviated pathway appears superimposed against the three-dimensional perspective scene outside the aircraft, where location highlighters are used for the depiction of the pathway comprising of at least one enhanced boundary of the active path, the second waypoint, the third waypoint, and the flight path formed between the second and third waypoints.

Abstract: A display system is provided that renders a horizontal situation indicator that includes required navigation performance (RNP) and estimated position uncertainty (EPU) values rendered non-numerically and in a fairly intuitive manner. A processor receives at least data representative of a desired course of the aircraft, data representative of the RNP for the aircraft, and data representative of the EPU for the aircraft. The processor renders, on a display device, a horizontal situation indicator that includes an aircraft symbol representative of a top-down view of the aircraft, an RNP boundary graphic representative of at least one RNP boundary for the aircraft, and an EPU graphic representative of the EPU for the aircraft. The aircraft symbol is rendered at a position that is representative of actual aircraft position relative to the desired course, and the RNP boundary graphic is rendered at a position relative to the rendered aircraft symbol.

Abstract: A flight management system (FMS) for an aircraft, that includes an integrated barometric altitude and satellite altitude-based vertical navigation (VNAV) system. The integrated barometric altitude and satellite altitude-based vertical navigation system, includes an altitude blending component for providing a smooth transition from a barometric altimetry source to a satellite altimetry source; and, a satellite altitude containment component operatively connected to the altitude blending component for limiting the difference of a barometric altitude path deviation to within a desired margin of a satellite altitude path deviation.

Abstract: The embodiments disclosed herein present novel and non-trivial system, module, and method for creating a variable FOV image presented on a HUD combiner unit. A processor receives navigation system data and data associated with eye position. A variable FOV image data set representative of navigation symbology is generated, where the image data set is determined by applying the navigation system and eye position data to an adaptive FOV function, where the function correlates eye position to an FOV image. The image data set is presented to a HUD system where an image represented in the image data set is displayed on a combiner unit, whereby the image FOV correlates to eye position. Furthermore, the processor may receive terrain data and generate a variable FOV image data set inclusive of data representative of a three-dimensional perspective scene outside an aircraft.

Abstract: A landing assistance device and method for an aircraft according to the invention, based on the landing procedure rules attached to the runway, a lower threshold and an upper threshold of total energy acceptable for the aircraft are determined and the current total energy of the latter is compared with the thresholds.

Abstract: A flight deck display element for an aircraft includes a primary flight display rendered thereon. The primary flight display includes a primary display region having a perimeter, a perspective view of terrain corresponding to a flight deck viewpoint, and an attitude frame surrounding the perimeter of the primary display region. The perspective view of terrain is rendered in the primary display region, and the attitude frame includes a first region and a second region rendered with different visually distinguishable characteristics. The boundaries of the first region and the second region are defined by a current attitude condition of the aircraft.

Abstract: An aircraft display system is provided that is configured to render a perspective display having a field of view. The aircraft display system includes a monitor and a processor coupled to the monitor. The processor is configured to generate a map display on the monitor. The map display indicates the value of at least one parameter of the field of view of the perspective display.

Abstract: An aircraft communications system is located on an aircraft. The aircraft communications system comprises a set of eyewear units, an aircraft data processing system, and a wireless system. Each eyewear unit has a set of sensors and a display. The set of eyewear units is capable of receiving user input and is capable of presenting information to a set of users of the set of eyewear units. The aircraft data processing system is capable of receiving the user input and sending the information to the set of eyewear units in response to receiving the user input from the set of eyewear units. The wireless system is located proximate to the cabin of the aircraft and is capable of sending the user input from the set of eyewear units to the aircraft data processing system and sending the information to the set of eyewear units.

Abstract: Technologies are described herein for displaying runway status information to a pilot in an aircraft. In one aspect of the present disclosure, a runway status display module displays a runway status indicator indicating the runway status information at a fixed scale independent of a scale of the map on a map display. In another aspect, the runway status indicator is displayed on a non-map display indicating the runway status of the runway. In another aspect, the runway status indicator is displayed at a position independent from a depiction of the runway on the aircraft display.

Abstract: A guidance system includes a device to generate an alphanumeric identification characteristic, enabling identification of a data item which is used for a selected guidance mode of an aircraft. The system also includes a display unit which automatically shows the alphanumeric identification characteristic on a display screen.

Abstract: A system and method uses light signals to detect and display the position of an airborne vehicle, such as a helicopter, during takeoff or landing or low speed, low altitude operation. A transmitter on the vehicle emits light signals while an optical receiver retrieves reflected light signals. Using light detection and ranging techniques, various parameters, such as altitude, ground speed and relative wind, are calculated based on the Doppler shift within the reflected light signals. The signals are transmitted in three different directions to facilitate the measurements of different Doppler shifts. The parameters are also displayed on a screen or other visual device within the vehicle.

Abstract: System and method increase the visibility of critical flight information on electronic displays. An aircraft display system includes a processing unit, a flight management system, a navigation system, a database for storing target data and terrain data, a graphics display generator, and a visual display. The flight management system and/or the navigation system provide real-time aircraft operational and flight control information. The processing unit directs the graphics display generator to generate graphic control signals for the visual display, which increase the transparency of a segment of a zero pitch reference line in the vicinity of a flight path marker on the display.

Abstract: A method is provided for indicating the boundaries of a required navigational performance (RNP) corridor on an aircraft's map display. The method includes the steps of producing an aircraft leg segment symbol on the map display, establishing an RNP value, and scaling the RNP value to the map display field of view. The method further includes the step of generating an RNP corridor boundary graphic on the map display offset from the aircraft leg segment symbol by the scaled RNP value.

Abstract: Systems and methods for direct communication between aircraft for one or more embodiments are adapted to receive tactical and strategic information related to proximate aircraft for improved flight planning. The systems and methods presented herein may be implemented, for example, in a first aircraft having a data link component adapted to process information, a storage component adapted to store information related to the first aircraft, and a communication interface component adapted to directly communicate with a second aircraft via a communication link. The first aircraft may include a user interface component adapted to interact with the data link component to retrieve information related to the first aircraft from the storage component, generate a request message with the information related to the first aircraft, and communicate with the communication interface component to directly transmit the generated request message to the second aircraft via the communication link.

Abstract: A display system for an aircraft includes an automatic reconfiguration device that, upon detecting a failure of a screen of the system, displays an image that is associated with the failed screen on an associated valid screen having lesser priority.

Abstract: The aircraft includes: means for causing data of a predetermined type to be stored on board solely in one or more memories; and automatic means for acting, when a predetermined event occurs, to destroy the data stored in this way.

Abstract: A flight management system for an aircraft, for executing a flight plan comprising referenced waypoints comprising a start point, an end point and intermediate waypoints, the said aircraft having a specified fuel quantity at the start of the said flight plan, executes a function of monitoring the fuel consumption with respect to at least one threshold value. The function comprises an operation for estimating if the quantity of fuel remaining on board drops below a threshold at any point in the flight plan included between the start point and the end point, and inserts a corresponding pseudo-waypoint in the flight plan, corresponding to the point where the said threshold is passed. The inserted pseudo-point is displayed on screens for displaying the flight plan.

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 for displaying aircraft glide slope includes determining a glide slope deviation that is representative of a difference between a desired aircraft glide slope and an actual aircraft glide slope. A glide slope icon that is representative of the desired aircraft glide slope and a glide slope deviation icon that is representative of the determined glide slope deviation are simultaneously rendered on a display.

Abstract: A display system for an aircraft includes a device for controlling the presentation on a head-down screen of primary piloting information during a detected display defect on a head-up display device, which normally displays such primary piloting information.

Abstract: An electronic flight bag for use aboard an aircraft during flight is disclosed. The electronic flight bag includes an electronic storage device which acts as a container for storing various user-configurable flight-related objects, such as flight routes as defined by way-points, airport information that includes approach routes, associated fight charts or other desired charts, temporary flight restrictions, and weather information as well as any other user-defined data objects associated with the flight. For example, the electronic flight bag may be used in corporate aircraft and may include one or more data objects that relate to the corporate policies with respect to flights. The data objects may also include time-sensitive data and contain time flags that can be updated by way of a communication link during flight. In accordance with an important aspect of the invention, the data objects are user-configurable so that a user can include virtually all information that is relevant to a particular flight.

Abstract: An aircraft standby display device includes a set of data sources, a data processing unit, and a display. The display presents altitude control indicators representing speed, altitude, attitude, and a heading scale that includes a characteristic symbol indicating a next route point of an aircraft flight plan. The heading scale is independent of the altitude control indicators. The display also presents a quantitative value that: (1) indicates the remaining distance of flight of the aircraft to reach the next route point and (2) is associated with the characteristic symbol.

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.