Abstract: An identifying device includes a vertical direction speed calculation unit configured to calculate a speed in a vertical direction of an air pressure measurement unit from an air pressure value measured by the air pressure measurement unit, the vertical direction speed determination unit configured to determine a magnitude of the speed in the vertical direction, a vertical direction continuous distance calculation unit configured to calculate a continuous distance of movement in the vertical direction based on the speed in the vertical direction calculated by the vertical direction speed calculation unit and the determination result of the vertical direction speed determination unit, and a vertical direction movement determination unit configured to determining whether the air pressure measurement unit is moving in the vertical direction or not in accordance with whether or not the vertical direction continuous distance is more than a predetermined threshold value.

Abstract: A method and device for calculating a safe path from a current position (P1) of an aircraft to an attachment point (P2) over a terrain. The current position (P1) of the aircraft is determined, and then the attachment point (P2) is defined. At least one attachment path connects he current position (P1) to the attachment point (P2) in safe manner over the terrain. The attachment path may be subdivided into a plurality of tracks (31-39). Each track (31-39) is situated at a safe altitude that is higher than the highest point of the terrain being overflown. In addition, the attachment path may be a return path defined by passage points (S1-S8) of the aircraft.

Abstract: A multi-layered edge computing method for aircraft monitoring and analysis includes providing an aircraft having a plurality of sensors connected to a flight data acquisition unit (FDAU), and providing a processing device having a processor, a non-transitory computer-readable memory, and a transmitter, wherein the processing device is in communication with the FDAU, wherein sensor data stored within the FDAU is communicated to the processing device, wherein, during flight of the aircraft, the processor analyzes the sensor data from the FDAU to detect an occurrence of at least one emergency event. The processing device ranks the at least one emergency event for transmission priority according to sensor type and severity and provides a signal transmitted to a flight control authority upon ranking of the at least one emergency event, wherein the signal has an alert sequence according to the ranking.

Abstract: A technique for reducing altitude error involves determining a corrected altitude for an aircraft using forecast atmospheric pressure data available, for example, from a weather forecasting service. The forecast atmospheric pressure data includes, for a number of points in time and for a number of geographic locations, a set of pressure levels and corresponding altitude values. Altitude correction data is periodically calculated from the forecast atmospheric pressure data for each of a number of geographic grid points. Upon receiving aircraft position information and an aircraft altitude measurement for an aircraft, one or more of the geographic grid points corresponding to the aircraft position are identified, and a corrected altitude of the aircraft is determined based on the altitude correction data of the one or more geographic grid points.

Abstract: An aircraft system includes a deviation module and a visual display. The deviation module is configured to receive a flight plan with a flight segment to a waypoint, the flight plan including a lateral profile, a vertical profile, and a time profile, the time profile including a predetermined time of arrival associated with the waypoint, receive a current lateral position and a current altitude, estimate an estimated time of arrival associated with the waypoint, compare the current lateral position to the lateral profile to generate lateral deviation, compare the current altitude to the vertical profile to generate vertical deviation, and compare the predetermined time of arrival to the estimated time of arrival to generate time deviation. The visual display is coupled to the deviation module and configured to display deviation symbology representing the lateral deviation, the vertical deviation, and the time deviation.

Abstract: A micro-computer based aircraft system that creates aural messages based upon system-detected threats (e.g., low oil pressure). The messages are unique to the make and model of aircraft. Speech recognition allows the pilot to request aircraft-specific, customized aurally-delivered checklists and to respond via a challenge and response protocol. This permits a hands-free, timely, complete and prudent response to the threat or hazardous situation, while allowing the pilot the relative freedom to do what is paramount: first, fly the airplane (with minimum distraction).

Abstract: A navigation aid information display device of an aircraft and primary flight display for an aircraft are disclosed. In one aspect, the navigation aid information display system includes a display screen including at least one first display area configured to display a first altitude scale including graduations, the current altitude of the aircraft on the first scale, and a set altitude value. The graduations of the first scale are distributed on an arc of a first disc including a first needle centered in the disc and the first needle is configured to indicate the current altitude on the first scale. The distribution of the graduations on the arc is nonlinear and symmetrical relative to a graduation corresponding to the set altitude value and defines extension graduations decreasing from the set altitude value.

Abstract: Present novel and non-trivial system, device, and method for varying the visibility of symbols depicted in a vertical situation display (“VSD”). An image generator receives zone data and defines a plurality of zones, where the zone data is comprised of second image data representative of a non-VSD zone symbol(s) or feature data representative of a zone feature(s). First image data representative of a VSD is generated, where the VSD is comprised of at least one VSD symbol representative of a zone symbol or a zone feature located in one of the three zones. If the represented zone symbol or zone feature of a VSD symbol is located within a left zone or a right zone, the visibility of each VSD symbol is variable and dependent of its proximity to a center zone.

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 flight information system may include a plan vertical situation display. The plan vertical situation display may display a vertical view of a flight path of an aircraft. The plan vertical situation display may display at least one path symbol showing at least one of a current path of the aircraft, a modified but not executed route of the aircraft, and an inactive route of the aircraft. The at least one path symbol may be adapted to display each of the current path of the aircraft, the modified but not executed route of the aircraft, and the inactive route of the aircraft. The plan vertical situation display may further display at least one terrain symbol showing a vertical terrain in the flight path along the at least one path symbol.

Abstract: A system and methods for generating alerts in a terrain awareness and warning system (“TAWS”) in an aircraft, using data acquired from a forward-looking radar The system comprises a forward-looking imaging device, an airport database, a navigation system, a forward-looking terrain alert (“FLTA”) processor, and a crew alerting system. The FLTA processor determines a measured clearance altitude of a highest cell within an area and compares it with a required minimum clearance altitude; if the measured altitude is equal or less than the required altitude, the crew is alerted. Alternatively, a terrain database may be used. with the FLTA processor for determining if the aircraft descends below the minimum operating altitude or is predicted to do so and then generating an alert. A method is disclosed for generating TAWS alerts using elevation angle measured by the forward-looking radar and terrain data retrieved from a terrain database.

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: A method for automatically detecting an erroneous height value supplied by a radio altimeter mounted on an aircraft. The method includes measuring, during the aircraft's approach phase with a view to landing, the duration between the times when a first predetermined altitude threshold and a second predetermined altitude threshold are reached. This duration is measured by taking into account current height values supplied by the radio altimeter. The method then includes comparing the measured duration to a predetermined duration reference time, which is lower than a flight duration that would allow the aircraft to descend from the first predetermined altitude threshold to the second predetermined altitude threshold at a maximum vertical speed. An erroneous height value is detected if the measured duration is lower than the predetermined duration reference time.

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

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: A method and apparatus for presenting information to operate an aircraft over terrain. A vertical profile view of the terrain is displayed relative to a location of the aircraft. A number of curves are displayed on the vertical profile view. The number of curves identify a climb capability for the aircraft based on a potential state for the aircraft.

Abstract: The invention relates to an aircraft navigational aid system with 3D display including an anti-collision device, with means of storing data representing obstructions, means for calculating a representation of the obstructions in a three-dimensional space and a device for displaying the obstructions data in three dimensions. The system includes means for augmenting the display of the representation of the area of hazardous obstructions with at least two indicator objects for the said area of hazardous obstructions disposed together in such a manner as to form a third object targeting the localization of the point in the area of hazardous obstructions closest to the aircraft. The invention also relates to the method of display of the indicator objects in a three-dimensional display.

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 advantageous embodiments provide a method and apparatus for presenting information to operate an aircraft over terrain. A vertical profile view of the terrain is displayed relative to a location of the aircraft. A number of curves are displayed on the vertical profile view. The number of curves identifies a number of maximum heights of the terrain that the aircraft can clear based on a current state of the aircraft.

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: According to the invention, the device (1) comprises means (3) for detecting, during an altitude capture maneuver, the emission of a first type alarm by the anti-collision system (2) and means (4) for controlling the vertical speed of said airplane (AC), after the emission of such an alarm, until the triggering of the capture phase.

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: According to the invention, the device (1) comprises means (4) for adapting the altitude capture maneuver, means (5) for first detecting the emission of a first type alarm, means (6) for determining a first alarm threshold and means (7) for establishing an activation height threshold from said first alarm threshold and airplane vertical speed at the time of the alarm emission, so that, when the height separating said aircraft (AC) from the altitude set level is strictly higher than said height threshold at the time of the alarm emission, said adaptation means (4) are disabled.

Abstract: A method and device performs onboard monitoring of a horizontal position of a taxiing aircraft, in which the monitoring of the horizontal position is based on separately determined height differences of the aircraft. A predetermined threshold value is compared with a first height difference calculated using repetitively determined first current height positions received by an onboard positioning device over a first duration. The predetermined threshold value is also compared with calculated second height differences calculated from two successively measured second current height positions determined by an altimeter over a second duration that is less than or equal to the first duration. A warning signal, signaling a problem with the reliability of the monitored horizontal position of the taxiing aircraft, is emitted in the event none of the second height differences is greater than the threshold value, and the first height difference is greater than the threshold value.

Abstract: A system configured for viewing meteorological data and generating said alerts in an aircraft. The system includes a navigation screen configured to display meteorological data in a monitoring plane at a determined altitude (Zs), and an altitude determination unit configured to determine the current altitude (Zp) of the aircraft. A processor is configured to determine the difference in altitude (Dz) between the aircraft's current altitude (Zp) and the altitude of the monitoring plane (Zs). The determined altitude difference (Dz) is compared with a first predetermined deviation threshold (S1), and a first alert (A1) is emitted under conditions in which the altitude difference (Dz) attains or exceeds the first predetermined deviation threshold (S1) and the altitude difference (Dz) diverges.

Abstract: A method and apparatus for displaying aircraft information. A selection of a piece of dynamic information is detected about an aircraft on a first display on a user interface. The piece of dynamic information is used to operate the aircraft and changes during operation of the aircraft. The piece of dynamic information selected from the first display is added to a custom display on the user interface. The custom display is displayed on the user interface on a display system for the aircraft.

Abstract: An altitude switch limit assembly has two independent limit switches to monitor cabin pressure and back up performance of the auto and monitor channels on the aircraft. The auto channel closes a first switch upon sensing that a cabin pressure falls below a set value, the monitor channel closes a second switch upon sensing that the cabin pressure falls below the set value. A first independent limit switch may be wired to the auto channel and a second independent limit switch may be wired to the monitor channel. Logic circuitry may determine that the assembly closes an outflow valve regulating cabin pressure when either both independent limit switches sense the condition, or when one of the independent limit switch senses the condition and either the auto channel or monitor channel to which that independent limit switch may be wired senses the same condition.

Abstract: Systems and methods for differential altitude estimation utilizing spatial interpolation of pressure sensor data are provided. In one embodiment, a method for mobile navigation comprises: measuring a horizontal location of a mobile navigation unit to generate two-dimensional horizontal coordinate data; measuring a barometric pressure at the mobile navigation unit with a sensor to obtain local pressure data; processing information representative of pressure data derived from a network of a plurality reference stations to obtain a correction factor; performing a calculation using the two-dimensional horizontal coordinate data, the local pressure data, and the correction factor to calculate an altitude coordinate; and determining an altitude of the mobile navigation unit from the altitude coordinate.

Abstract: Disclosed is a method and device, which provide an enhanced ability to monitor the navigation of an aircraft during a phase of flight in which the aircraft is close to the ground in which the aircraft uses positional information supplied by a satellite positioning system for the navigation. A display screen is used to display a first characteristic sign representing a selected setpoint value for a height parameter of the aircraft. The display screen also displays a second characteristic sign representing a current auxiliary value expressed in the form of an achievable height parameter. An alert is emitted when the second characteristic sign is determined to be within a predetermined height value of the first characteristic sign, and the alert is shown in visual format on the display screen. An alarm is also emitted following a predetermined time after the alert is emitted, if the setpoint value is not replaced by a new setpoint value.

Abstract: Systems and methods for performing efficient, inexpensive data logging of aircraft sensor data. An example system on board an aircraft includes a plurality of data sources that provide sensor data associated with a plurality of avionic components, a line replaceable processing unit that is in signal communication with the plurality of data sources via one or more databuses, a wireless router connected to the line replaceable processing unit via a data cable and a portable data unit in wireless data communication with the wireless router. The wireless router receives at least a portion of the sensor data from the line replaceable processing unit and sends the received sensor data to the portable data unit.

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 system for presenting visual features to a pilot of an aerial vehicle contains a flight display. The flight display includes a display screen, a programmable device, an input device, and a memory. A plurality of visual features is contained in the memory. A plurality of feature characteristics is contained in the memory. Each of the feature characteristics is linked to at least one of the features. An environmental device communicates with the input device. The environmental device inputs an approximately present environmental condition of the aerial vehicle to the input device. The programmable device compares the approximately present environmental condition to the feature characteristics to determine which of the features stored in the memory to display on the flight display.

Abstract: Systems and methods for performing efficient, inexpensive data logging of aircraft sensor data. An example system on board an aircraft includes a plurality of data sources that provide sensor data associated with a plurality of avionic components, a line replaceable processing unit that is in signal communication with the plurality of data sources via one or more databuses, a wireless router connected to the line replaceable processing unit via a data cable and a portable data unit in wireless data communication with the wireless router. The wireless router receives at least a portion of the sensor data from the line replaceable processing unit and sends the received sensor data to the portable data unit.

Abstract: The present general inventive concept relates to methods and systems to select and display information on an avionics display screen. The systems and methods allow for the selection and display of information using knobs to highlight and select the desired information for display, eliminating the need for a cursor function. The systems and methods also provide for multiple pages and/or multiple windows or “tiles” within these pages and/or windows simultaneously on a single screen of a display, with each window, page, and/or tile being fully controlled independently when selected. The present general inventive concept also relates to systems and methods to provide multiple cues on an electronic display system altitude tape to a pilot in advance and impending approach to a predefined altitude. The present general inventive concept also relates to systems and methods to employ variable resolution topographical data based on display range for an avionics navigation display.

Abstract: Methods and systems are provided for indicating whether an aircraft is below a designated minimum safe altitude level for an altitude sector. A method comprises displaying a graphical representation of a first sector on a display device associated with the aircraft. The first sector corresponds to a geographic area having a first minimum altitude criterion. If a current altitude of the aircraft is below the first minimum altitude criterion, the method continues by displaying the graphical representation of the first sector using a first visually distinguishing characteristic chosen to indicate that the aircraft is below the designated altitude level for the first sector.

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

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: A system determines a limit angle of climb corresponding to a climb angle of an aircraft for flying over the ground along an avoidance path and displays a characteristic sign representing the limit angle of climb on a display screen.

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 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: The invention relates to a system for signalling and locating vehicles involved in accidents, stopped vehicles and vehicles with mechanical problems in daytime and night-time conditions as well as in adverse weather conditions. According to the invention, the occupants of the vehicle can raise the alarm without leaving the vehicle such as to avoid any physical risk. The invention comprises a case and a hinged cover housing an air container. One end of the air container is connected to a gaseous fluid outlet pipe and to a manual quick-opening non-return valve which is located in the mouth of an empty aerostatic inflatable fluorescent body. The aforementioned body is folded inside the case when not in use and is deployed in the event of a vehicle impact by means of a device comprising an inertia sensor which is activated by a deceleration force exceeding 3G and which is powered by a power source comprising batteries or accumulators belonging to the electric circuit of the vehicle or independent batteries.

Abstract: A system and method for storing altimeter setting values on an aircraft display includes simultaneously rendering an altimeter and an active altimeter setting field, and selectively rendering a standby altimeter setting field simultaneously with the altimeter and the active altimeter setting field. An active altimeter setting value is rendered in the active altimeter setting field, and a stored altimeter setting value may be rendered in the standby altimeter setting field. Preferably, the stored altimeter setting value is selectively rendered in the standby altimeter setting field when the standby altimeter setting field is simultaneously rendered with the altimeter and the active altimeter setting field.

Abstract: A method of symbolically representing a location of an aircraft on a display in the aircraft is disclosed. It is determined whether the aircraft is operating proximal one of a runway and a taxi-way. A range of the display is selected. Features are displayed near a location of the aircraft on the display at a first scale that corresponds to the selected range. A first symbol representing a current location of the aircraft is displayed on the display at the first scale in solid form. A second symbol representing the current location of the aircraft is displayed on the display at a second scale in non-solid form when a size of the first symbol representing the aircraft at the first scale obscures the displayed features on the display. The size of the first symbol is smaller than a size of the second symbol.

Abstract: Methods and systems are provided for presenting procedure information for a vertical profile on a display device associated with an aircraft. A method comprises displaying a first segment of the plurality of segments comprising a vertical profile with a first vertical scale and a first horizontal scale, wherein the first horizontal scale is based on a first distance associated with the first segment. The method further comprises displaying a second segment of the plurality of segments with the first vertical scale and a second horizontal scale, wherein the second horizontal scale is based on a second distance associated with the second segment. The first horizontal scale and the second horizontal scale are not equal. In this manner, the vertical profile has a nonuniform horizontal scale and a uniform vertical scale across segments.

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: 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: An aircraft display and control system generally includes a processor, a cursor control and selection device, a multifunction keyboard, an aeronautical information database, a geographic database, and a plurality of display devices. Users, such as an aircraft pilot and copilot, can perform flight plan entry and modification by manipulating graphical and textual information on the display devices using the cursor control device and the multifunction keyboard. In one embodiment, the present invention provides an interface to flight deck information systems that is intuitive and easy to use, and which enables flight crew members to easily and effectively enter and modify data displayed by the aircraft flight deck, substantially centralizes avionics controls within one controller, and decreases flight crew “heads-down” time.

Abstract: The present invention is directed to a method of positioning perspective terrain on a SVS (Synthetic Vision System) based on a navigation solution, the vertical component of which is calculated utilizing a terrain database and sensing unit (which provides height above terrain). The terrain database provides elevation of terrain above MSL. A sensor, such as a GNSS sensor, may be utilized to calculate the navigation solution. In alternative embodiments, the navigation solution is calculated differently based upon the phase of flight. In one, the vertical component calculation utilizes the sensing unit at or below the sensing unit's rated altitude. In another, vertical component calculation blends the sensing unit with the sensor. The blending may be based upon percentages based upon altitude or utilize filtering such as Kalman filtering. The present invention is particularly advantageous for close to ground operations, insuring perspective terrain will stay consistent with the real world.

Abstract: A device to assist in an independent piloting of an aircraft at least in a descent phase includes a unit to determine a descent axis which assists a pilot in flying from a safe altitude to a decision height, the descent axis being secured relative to the ground being flown over, and a guidance system to assist in the guiding of the aircraft along said descent axis in a descent phase.