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: Methods and systems for a position indicating display system for an aircraft are provided. The system includes a map display unit configured to display a map representative of an area being traversed by the aircraft, and an overlay comprising an own ship depiction, said overlay displayed on the map for a period of time in response to an input from at least one of a user and an aircraft sensor.

Abstract: A visual aid is used by a pilot in an aircraft to position himself in the cockpit by an axial movement, called movement along the X axis, in an aircraft reference coordinate system, and by a vertical movement, called movement along the Z axis, in the aircraft reference system. The visual aid comprises two geometric shapes (3, 4), separated in space and designed to be visually aligned by the pilot; these shapes have the characteristic that each has a visual reference (31, 41) on its surface, approximately in the same horizontal plane perpendicular to the vertical XZ plane.

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: An avionics display is disclosed. A synthetic rendering of terrain is created using stored terrain data. A horizon line is overlaid upon the synthetic rendering of terrain. The horizon line represents zero degrees pitch attitude in a direction of travel of an aircraft in which the avionics display is installed. The horizon line is configured to move in response to attitude-changing movement of the aircraft. An attitude cue is overlaid upon the synthetic rendering of terrain and depicted on first and second sides of the horizon line such that the synthetic rendering of terrain remains substantially visible. The attitude cue has a first appearance on the first side of the horizon line and a second appearance on the second side of the horizon line. The first appearance is visually contrasted from the second appearance.

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: The system contains a receiver in communication with a programmable device. The receiver receives a first horizontal distance from the aircraft to a threshold of the runway, an angle of a glide path, and a threshold crossing height. The programmable device determines a projected ground distance from the aircraft to the threshold. The programmable device determines a projected ground distance from the threshold to a glide path intercept point. The programmable device determines a vertical value along the glide path relative to a projected ground distance between the aircraft and the glide path intercept point. The programmable device determines a synthetic altitude above runway for the aircraft.

Abstract: The display system (1) comprises means (6) for controlling the presentation on a head-down screen (E1 to E3) of primary piloting information, during a defect of display on a head-up display means (3) which carries out the display of such primary piloting information.

Abstract: An electromagnetic emissions free optical signal based helicopter landing assistance arrangement wherein helicopter rotor wash dust cloud-caused obfuscation of the intended landing site and other landing threats are overcome. Real time optical sourced data is collected early and used during helicopter approach to the intended landing site. Upgrading of this data for use during dust cloud presence is accomplished with image processing techniques applied in response to such inputs as helicopter flight data. Military use of the invention especially in current theatre conflict environments is contemplated. Dust cloud related landing hazards are disclosed as a significant difficulty in such environments and generate need for the invention.

Abstract: A method, system and computer program product to detect and indicating TFR zone violations, potential TFR zone violations or TFR zones in vicinity of an aircraft and indicating measures to avoid or exit a TFR zone are provided. TFR zone information and an aircraft's position information are received. The aircraft's position information is processed to determine the aircraft's current heading. A TFR zone violation is determined based on the aircraft's current position. A potential TFR violation is determined based on whether the aircraft's current heading intersects a TFR zone. The presence of a TFR zone in the vicinity of the aircraft is determined based on the aircraft's current position and heading. Indicators of a TFR violation, potential TFR violation, no TFR violation or TFR zones in the vicinity are provided. If a TFR violation, or possible TFR violation or TFR zone in the vicinity are found, measures are indicated to exit the TFR zone or change the aircraft's current heading to avoid the TFR zone.

Abstract: A flight control indicator for an aircraft has a set of information sources, a computation unit which determines, on the basis of information emanating from the set of information sources, an item of information regarding actual thrust of an engine of the aircraft, and a display device which is a head-up display device and which presents, on a display screen, an indication of the item of information regarding actual thrust. The item of information regarding actual thrust is associated with a thrust scale and both are presented superimposed on the environment prevailing in front of the aircraft.

Abstract: Systems and methods are provided for integrated control, access, and customizable presentation of navigation related, flight information data on a multifunction display (MFD) within a cockpit. The MFD includes a bezel having controls located thereon which are adapted for controlling display formats, communication devices, navigational devices, and equipment sensors. A display is located adjacent to the bezel. The display is adapted to include at least one display region having navigation related data. At least one of the controls is operable to variably select a display format for the at least one display region.

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: A weather briefing system that may be used in the cockpit to provide near real-time graphic and text weather information. Weather information and pilot reports are fed to the cockpit from, e.g., a satellite in geosynchronous orbit. Once delivered to the aircraft, the system processes the data stream and formats it for delivery to an end user device. The data is collected from an extensive network of sources. The end user device may be a portable electronic flight bag (EFB), panel-mounted display (MFD), or similar device programmed to display the formatted data. The system provides timely and accurate weather information to pilots of all types of aircraft. This information may be used for pre-flight planning and in-flight decision-making.

Abstract: Techniques for representing a holding pattern on a vertical situation display are described. The vertical situation display has a first screen area to depict the holding pattern and second screen area to show a flight path after the holding pattern. The representation of the holding pattern visually informs a flight crew of current and prospective flight conditions.

Abstract: A display system and method for an aircraft simultaneously displays the terrain under the flight plan, or under the current track of the aircraft, as both a two-dimensional lateral situation view image and as a perspective vertical situation view image. This provides improved tactical flight planning, and that does not erroneously show the flight plan passing through the displayed terrain.

Abstract: The invention concerns a device comprising a set of data sources, a data processing unit, and a display which presents on a display unit (8) altitude control indicators (9, 10, 11) representing at least speed, altitude and altitude data of the aircraft and a heading scale (12) including a characteristic symbol (13) indicating at least one next route point of the aircraft flight plan, said heading scale (12) being independent of said altitude control indicators (9, 10, 11), as well as a quantitative value (14) which indicates the remaining distance of flight of the aircraft to reach said next route point and which is associated with said characteristic symbol (13).

Abstract: The invention relates to an aircraft navigation aid method.

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 head-up display (HUD) is disclosed. The HUD is provided on board an aircraft. The HUD comprises a projector and a combiner. The combiner enables viewing of the world outside of the combiner and also allows viewing of information provided from the projector. A computer is coupled to the projector and provides airport runway and taxiway symbols conformally mapped onto the combiner. Also provided on the combiner is a mapping of hold lines onto the combiner.

Abstract: A measurement system for an aircraft having the three-axis components of the airspeed of the aircraft, the three-axis components of the wind speed currently encountered by the aircraft, and the wind speed distribution ahead of the aircraft simultaneously in real time. It comprises a Doppler anemometer measuring the airflow speeds at a plurality of points separated by a prescribed distance in the beam irradiation direction that changes in a time series, and an inertial data measurement device measuring the movement information and positional information of the aircraft. Moreover, the display system of the aircraft includes the horizontal two-axis airspeed of the aircraft, the three-axis components of the wind speed currently encountered by the aircraft, and information on the wind speed distribution ahead of the aircraft are displayed simultaneously in real time.

Abstract: The system contains a receiver in communication with a programmable device. The receiver receives a first horizontal distance from the aircraft to a threshold of the runway, an angle of a glide path, and a threshold crossing height. The programmable device determines a projected ground distance from the aircraft to the threshold. The programmable device determines a projected ground distance from the threshold to a glide path intercept point. The programmable device determines a vertical value along the glide path relative to a projected ground distance between the aircraft and the glide path intercept point. The programmable device determines a synthetic altitude above runway for the aircraft.

Abstract: A method for landing an aircraft includes determining the aircraft's deviation from its approach path so as to define a first point of the aircraft's heading. A first straight line passing through the first point and through a second point defining the ground orientation of the approach path is displayed, by a head-up display, on a horizon line with a heading scale. The first straight line represents a ground plot of the approach path. A first assistance gate is displayed such that the first straight line passes through the first assistance gate when the aircraft is aligned on the approach path. A second straight line, parallel with the horizon line and passing through the first point, is displayed and represents a plot on the ground of the origin of the approach path. A second assistance gate is displayed under the horizon line and represents the slope of the approach path.

Abstract: The information relates to a method of transmitting information between a communications management unit on board an aircraft and a ground air control system, characterized in that it comprises the following steps consisting, in respect of the communications management unit, in: a) detecting the reception of alerts originating from an onboard surveillance system, via a communication bus, b) when an alert is detected, shaping the information contained in the alert as a report according to a predetermined format, and dispatching this report to the ground system.

Abstract: This onboard flight management system displays on the navigation screen the plots of the flight plan parts corresponding to the navigation procedures whose names are displayed on the MCD console during the introduction by the crew of the aircraft, by means of the MCD console, of the elements allowing the FMS flight management computer to plot a flight plan. This facilitates the task of the crew when choosing navigation procedure since the plot of the flight plan part corresponding to a navigation procedure is much more expressive than the name of the procedure.

Abstract: Presented herein is a system that enables a vehicle operator to record continuous images of surrounding traffic activity, wherein the vehicle is equipped with a video camera 20 for continuously recording the vehicle surroundings. The system further comprises a marking switch 42 that enables the vehicle operator, upon viewing a possible traffic violation, to trigger a marking module 40; a marking module 40 that identifies and marks, in real-time, at least one location of the video recording that relates to the at least one possible traffic violation committed by at least one other vehicle operator; a portable storage device 30; an editing module 50 for preparing recorded segments for transmission, which include at least one recording portion that appears before the added mark and at least one recording portion that appears after the added mark; and a communication module 60 for transmitting the prepared recording segments to a designated server.

Abstract: A method and corresponding system remotely communicate and interface with an Aircraft Condition Monitoring System (ACMS) on an aircraft. The method and system offer a global communication architecture that can be implemented with existing ACMS devices and with any flight data acquisition unit (FDAU) equipped with a storage card, such as a Personal Computer Memory Card. International Association (PCMCIA) card. In a preferred embodiment, the method and system offer real-time wireless communication between the ACMS on an aircraft and a ground station without any hardware and/or software modifications to the ACMS.

Abstract: These teachings present triple data transport redundancy in the form of three data bus interfaces that are each designed and manufactured independently from one another and compatible with a common data handling protocol. This protocol can be one that includes no error correction. These interfaces can each couple to a corresponding first, second, and third data bus that may comprise optical data busses. Information gauges can be realized through use a memory that stores a plurality of images comprising views of an information gauge (or gauges) of interest showing a variety of different readings. Upon receiving information regarding a monitored parameter of interest (via, for example, the aforementioned data busses and data bus interfaces), this information can be used to address the stored information gauge view that corresponds to the present parameter value. That particular view can be recalled and displayed to thereby provide the corresponding information to a viewer.

Abstract: Methods, data structures, and systems are provided for configuring avionic equipment with profile data. Profile data is defined, stored, and/or retrieved. The profile data is used to configure one or more display fields of the avionic equipment, display units of measure, identify flight plans, define map settings, set navigation fields, define communication transceiver spacing, define data/time setup, to configure one or more timers, alarms, and/or to configure other communication, navigation, or surveillance settings associated with avionic equipment. Furthermore, instances of the profile data are associated with unique identifiers for storage and retrieval purposes.

Abstract: A wireless communications system, and a corresponding method, for use with an aircraft, includes airborne pico cell base stations mounted on the aircraft, the base stations capable of communication with wireless devices used by subscribers on the aircraft via using switching/transaction processing equipment located optionally on the aircraft or in the ground network with one or more ground-based networks. The system includes aircraft location equipment, in communication with the base stations, that determine the aircraft's location, including latitude, longitude, altitude, and other relevant data. Finally, the system includes a wireless communications enable/disable module that receives the aircraft's location and enables and disables wireless communications through the base stations based on the aircraft's location.

Abstract: A method of dynamically displaying lateral deviation in formats on a display is provided. The method comprises assigning one or more positional boundaries for displaying the lateral deviation information, wherein the one or more positional boundaries define areas on a display. The method also comprises calculating display positions of a lateral deviation symbology and determining if each calculated display position is allowed based on where the lateral deviation display would be located, if displayed at each calculated position, in relation to the one or more positional boundaries. The method further comprises, displaying the lateral deviation symbology at the calculated positions when the calculated positions are allowed, and displaying a lateral deviation indicator when the calculated positions are not allowed.

Abstract: The invention relates to a device (1) comprising a set (2) of information sources for determining the active values of a plurality of parameter of an aeroplane, calculating means (3) for determining, by means of said active values, a first position corresponding to a position which is extrapolated from the nose of the aeroplane following a particular time interval from the current instant. The inventive device also comprises a database (5) provided with at least one pre-determined unauthorized zone of the airport, comparison means (6) for comparing said first position to said pre-determined unauthorized zone of the airport, and warning means (9) for emitting at least one warning signal if the first position is located in the unauthorized zone.

Abstract: Methods, data structures, and systems are provided for configuring avionic equipment with profile data. Profile data is defined, stored, and/or retrieved. The profile data is used to configure one or more display fields of the avionic equipment, display units of measure, identify flight plans, define map settings, set navigation fields, define communication transceiver spacing, define data/time setup, to configure one or more timers, alarms, and/or to configure other communication, navigation, or surveillance settings associated with avionic equipment. Furthermore, instances of the profile data are associated with unique identifiers for storage and retrieval purposes.

Abstract: A head-up display (HUD) is disclosed. The HUD is provided on board an aircraft. The HUD comprises a projector and a combiner. The combiner enables viewing of the world outside of the combiner and also allows viewing of information provided from the projector. A computer is coupled to the projector and provides airport runway and taxiway symbols conformally mapped onto the combiner. Also provided on the combiner is a mapping of automatic dependent surveillance broadcast advisory information and traffic onto the combiner.

Abstract: A flat panel display system for an aircraft display includes a graphics rendering computer for rendering of anti-aliased graphical imaging data derived from aircraft sensors for full-field imaging on a cockpit display screen. A comparator processor independently generates, from the same sensor data, a selected subset or “points of light” of the display screen image and compares the points of light data to the data generated by the rendering computer for the same display screen pixel locations. The minimized processing requirements and simplified design of the comparator processor enable ready FAA certification of the comparator processor, whereas the extreme complexity and processing operations required of the rendering computer make FAA certification thereof unusually time consuming and expensive.

Abstract: A method, computer software product, and system to generate altitude callouts according to proximity to a runway at an airport or heliport includes determining whether the helicopter is flying in proximity to the runway and automatically selecting an altitude threshold increment set based upon the determination. The threshold increment set including a plurality of altitude threshold values. A calculated terrain clearance value is calculated for each of the plurality of altitude threshold values. A suitable warning is automatically generated according to the comparison. Selecting an altitude threshold increment set includes selecting one of the group consisting of first altitude threshold increment set including a plurality of higher altitude threshold values and a second altitude increment set including the plurality of higher altitude threshold values and further including a plurality of lower altitude threshold values.

Abstract: Methods and systems for displaying aircraft operations information are disclosed. A method in accordance with one embodiment includes receiving operations information, presenting a first portion of the information over a first area of a display medium having a first size, receiving a signal corresponding to an instruction to increase a fraction of the display medium occupied by the operations information, and presenting at least the first portion of the operations information over a second, larger area of the display medium. Multiple display media can be controlled by independent selectors, with each selector having two portions, one to select categories of aircraft operations information, and another to present groups of selectable options corresponding to each of the individual categories of operations information.

Abstract: Method and device for predicting the stopping position of an aircraft whilst landing. According to the invention, said stopping position (Mr) is predicted from the variation of total energy of said aircraft (5) before the beginning of the flare out (6a) of the latter.

Abstract: A display system for a device with reduced out-the-window visibility includes a display processor that receives an image from a sensor, wherein the sensor is capable of providing a continuously updated image of an area outside the device that is obscured from view of an operator by a portion of the device's structure. The sensor image can be combined with symbols representing information regarding the operational state of the device. The combined sensor image and symbols are output to a display device that is positioned to provide a portion of the out-the-window field of view to the operator. The entire desired field of view for the operator is provided by the display device in combination with the out-the-window scene available through windows of the device.

Abstract: A flight instrument displays azimuth information in combination with horizon information and other optional information such as altitude and/or airspeed. Azimuth information is displayed using an elliptical pattern placed below a horizon line displaying horizon information. The horizon information may be based on gyro enhanced vertical speed and/or vertical axis information. The elliptical pattern may be representative of a horizontal circular heading indicator viewed from above and behind the circular indicator. In one embodiment, the elliptical azimuth pattern moves in response to movement of the horizon line to maintain position below the horizon line. Airspeed and/or altitude information may be displayed at the sides of the screen area using a circular arc display pattern.

Abstract: An improved system and method are disclosed for facilitating target aiming and aircraft control by flight crews using electronic displays. For example, an aircraft display system is disclosed that includes a database for storing target location and boundary data, a processing unit, a position and direction determination unit for use in determining the position of an aiming symbol on a display, a graphics display generator, and a visual display. The processing unit determines whether or not a selected target to be displayed is obscured or covered by the aiming symbol to be displayed. If any portion of the target is obscured or covered by the aiming symbol, then the processing unit directs the graphics display generator to generate graphic control signals for the visual display, which increase the transparency of the portions of the aiming symbol that obscure or cover the target.

Abstract: Apparatus and methods are provided for flight instruments in an electronic format. The flight instruments may appear in a standard configuration, including both primary flight instruments and secondary flight instruments. The apparatus and methods may also provide some or all of the primary flight instruments in one visual representation.

Abstract: Methods and systems for graphically displaying sources for aircraft flight control instructions are disclosed. A method in accordance with one embodiment of the invention includes displaying at a display medium a map of a region at least proximate to an aircraft and displaying an aircraft indicator at least proximate to the map. The aircraft indicator can identify current location of the aircraft, and its location relative to the map can be updated as the aircraft executes a flight. The method can further include displaying at least proximate to the map an indication of a current mode by which a path of the aircraft is currently being automatically controlled.

Abstract: Methods and apparatus are provided for displaying terrain data symbology for an aircraft. The apparatus is a heads-down display for an aircraft having a monitor configured to generate a display and a processor coupled to the display. The display has a centerline. The processor is configured to align the centerline of the display with a track of the aircraft, and generate on the display a first symbol corresponding to a terrain and a second symbol corresponding to an attitude of the aircraft. The processor is further configured to position the first symbol and the second symbol with reference to the track of the aircraft.

Abstract: A mileage display system includes a control unit operatively connected to an ignition switch of a motorcycle that obtains the accumulated mileage by accumulating a pulse signal produced according to running of the motorcycle. The control unit records odometer data in an EEPROM. The control unit also reads the odometer data recorded in the EEPROM when the ignition switch is operated. If the odometer data exceeds the maximum value to be displayed on an odometer (for example, 99999), the control unit displays on the odometer for a predetermined period of time a numeric value of digits of higher order than the predetermined number of display digits of the odometer data. The mileage display system displays an accurate, accumulated distance traveled or accumulated mileage, after the mileage overflows by exceeding a maximum display value as established by a predetermined number of display digits.

Abstract: An improved system and method are disclosed for indicating the validity of airport runway visual approach slope indicators on an aircraft display. An aircraft display system is provided, which includes a database for storing data about the specific visual approach slope lighting indicator system being used by each airport of a plurality of airports and any special distance and/or usage limitations associated with each such visual approach slope indicator system, a processing unit, a position determination unit, and a visual display. As an aircraft approaches an airport, the processing unit receives the aircraft's current position from the position determination unit, and compares the aircraft's current position data with the distance and/or usage limitation data stored in the database for the approach slope indicator system being used by that airport.

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: A timer usable in navigating and piloting an aircraft, the timer having a plurality of application modes for management of time and numeric data, including an approach mode, a fuel mode, a chronograph mode and a clock mode. Each application mode can drive independent but simultaneous time count sequences for use in flight management and navigation such as counting down approach times, fuel-tank switching intervals and other time sensitive events, as well as providing military time, standard time and UTC time.

Abstract: A process and device for detecting on an aircraft an overshoot of design loads at the level of a structural part of the aircraft. The detection device includes a speed measuring device for measuring an effective speed of the aircraft. A first comparator compares the measured effective speed with a maximum speed relating to the current flight configuration of the aircraft. A vertical load measuring device measures a vertical load factor of the aircraft, and a second comparator compares the measured vertical load factor with a limit value of the vertical load factor. An inspection determining device determines whether a structural inspection needs to be performed at the level of the structural part, based of the results of the first and second comparisons.

Abstract: Method and system for analyzing and displaying one or more present flight parameter values FP(t) of an aircraft in motion at a measurement time tn, and for comparing the present flight parameter value with a selected percentage band, containing historical flight parameter data for similar conditions.