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 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.

Abstract: A method and system for meteorological monitoring aboard an aircraft. According to the invention: the altitude difference between the current altitude of the aircraft and the altitude of the meteorological monitoring plane is formed; said altitude difference is compared with a predetermined deviation threshold; and a first alert is emitted if said altitude difference attains or exceeds said deviation threshold and if said altitude difference diverges.

Abstract: A system and method for filtering various targets (such as ground vehicles, stationary objects, and aircraft) from display on a display screen within the cockpit of an “Own Ship” aircraft. The system and method withhold from display any non-exempt targets that have an altitude that is either: (1) greater than an upper-threshold altitude; or (2) less than a lower-threshold altitude. The upper-threshold altitude and the lower-threshold altitude may be set to user-specified, customized values as desired to accommodate current flying conditions. In addition, the system and method may also be configured to operate in a plurality of operating modes, each of which features a different upper threshold altitude/lower threshold altitude combination. The system and method are preferably configured to reset certain threshold altitudes to pre-defined default altitudes in response to the aircraft landing.

Abstract: Systems and methods for monitoring Required Navigational Performance (RNP) Procedures and reducing nuisance Enhanced Ground Proximity Warning System warnings including a processor, a memory with RNP instructions and data, and a communication device. The processor accesses the RNP data and instructions from the memory, and uses the communication device to obtain flight information from a Flight Management System of an aircraft. When the processor determines that the aircraft is in RNP space, the processor projects an RNP envelope and modifies a warning envelope of an EGPWS to coincide with the RNP envelope if the EGPWS warning envelope extends farther than the RNP envelope.

Abstract: In distance maps used in order to facilitate the navigation of craft such as an aircraft, the distances estimated take into account obstacles to be circumvented but not the maneuverability of the craft. The adaptation route required by the craft in order to take the right direction is not taken into account so that certain distance estimates for accessible points located in the neighborhood of the craft are unrealistic. In order to make a distance map more realistic, it is proposed that an obstacle of concave shape associated with the craft be added behind the position of the craft, forcing the estimations of distances to be circumvented an area that is inaccessible to the craft for reasons of maneuverability.

Abstract: A method and device for detecting, on the ground, the obstruction of a pressure tap of a static pressure sensor of an aircraft. The device includes a pressure sensor that measures the pressure inside a probe and a heating system for heating the probe. When the heating system is activated, the sensor carries out a first measurement of a parameter dependent on the pressure inside the probe. After a predetermined duration from the activation of the heating system, the sensor carries out a second measurement of the parameter. A central processing unit calculates the difference between the first and second measurements and compares this difference to a predetermined value. A warning device emits a warning signal indicating the detection of an obstruction if the difference is greater than the predetermined value.

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 present invention provides a method and system for displaying critical navigational data on a primary flight display to a pilot of an aircraft. The method includes providing an image representative of weather information on a primary fight display and superimposing an image representative of a terrain warning indicator over at least part of the image representative of weather information.

Abstract: The present invention relates to a standby instrument fitted to the instrument panel of an aircraft detecting overloads. The standby instrument includes a processor to calculate and display flight information based on data provided by associated sensors integrated into a standby system. It additionally includes a module for detecting overload of the aircraft on the basis of the data provided to display the flight information. The invention applies to the detection of overloads during a heavy landing. More generally, it applies to the detection and indication of overloads of an aircraft in various types of environment.

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: The device relates to the signaling, to the pilot of a craft, of the risks that it incurs due to obstacles placed in its zone of deployment. This device determines, on the zone of deployment of the craft, the contours of several types of risk region as well as the contours of two lateral regions of tight deployment tied to the craft and produces alarms as a function of the types of zones at risk found in the lateral regions of tight deployment.

Abstract: This method uses for the estimation of a distance, a propagation distance transform considering only the paths which are both accessible to the aircraft taking account of its vertical flight profile and complying with air regulations. The propagated distance Dp is accompanied by a propagated altitude Ap which at all points follows the vertical flight profile of the aircraft, while being greater than the altitudes of these points and complying with the air regulation constraints at these points. This is obtained by subjecting the propagation to compliance with the vertical flight profile of the aircraft, constraints of the elevations of the points of the relief and air regulation constraints.

Abstract: A terrain awareness and warning system includes electronics for receiving radar returns and providing terrain and/or obstacle alerts or warnings in response to the radar returns. The electronics receives information from a database and the information is utilized to suppress false alerts or warnings.

Abstract: Systems and methods for controlling activation of a look-ahead function of a terrain alert and warning system. The system receives rate of climb and aircraft speed information, compares the rate of climb and aircraft speed information to a predefined threshold, and deactivates a look-ahead function based on the comparison.

Abstract: A safety enhancement warning system includes an avoidance system which communicates with a multiple of geographical positional systems. A geographic algorithm of the avoidance system utilizes a recursive algorithmic to determine if the aircraft will enter a sensitive area. If the aircraft distance to a sensitive area decreases below a predefined minimum threshold, then an audible and/or visual warning is issued. For certain sensitive areas, aircraft RF emissions are silenced or reduced in power when the predetermined minimum threshold breaches the sensitive area. The use of the avoidance system enables usage of relatively inexpensive UWB radar for the proximity sensor suite to assure avoidance of interference with particular delicate instruments and thereby meet regulations such as those propagated by the FCC.

Abstract: The present invention is directed to a traffic display for an aircraft, which includes a vertical traffic indicator. The vertical traffic indicator includes flight levels, depicted utilizing differing visual patterns to represent the current flight level as well as available and unavailable flight levels for transit. The vertical traffic indicator includes aircraft indicators positioned in relation to flight levels to indicate attitude. The aircraft indicators may also include status indicators indicating separation standards, vertical trend, intent, or whether an aircraft is a reference aircraft for an ITP. The traffic display provides clear and intuitive means of understanding the flying environment related to the performance of the ITP, increasing situational awareness and simplifying the ITP. The traffic display is specifically advantageous for performance of an ITP, but may be integrated with displays including terrain, weather, flight plan waypoints, or TCAS (Traffic Collision Avoidance System) traffic.

Abstract: Methods and systems are disclosed for preventing aircraft collisions with forward looking terrain avoidance (FLTA) functionality based on a terrain avoidance profile used to evaluate potential terrain threats based on the projected flight path of an aircraft in flight, and a clear terrain profile to determine whether the terrain threat has been cleared. If the terrain avoidance profile conflicts with terrain, a collision threat may exist whereby the pilot is notified and a terrain avoidance maneuver is executed. During the terrain avoidance maneuver the clear terrain profile extends in a direction substantially parallel with the horizon at or near the present altitude of the aircraft to check whether it is safe to return to the previous flight path angle or otherwise end the terrain-avoiding maneuver. When the clear terrain profile no longer conflicts with the terrain threat, a terrain clear indicator is then issued to the pilot.

Abstract: A primary flight display system is provided for deployment on an aircraft including a barometric altimeter and a secondary altitude-determining device. The barometric altimeter provides a first estimated altitude corresponding to a reference pressure setting, and the secondary altitude-determining device provides a second estimated altitude. The primary flight display system includes a primary flight display (PFD), and a controller coupled to the PFD. The controller is configured to generate: (i) an altitude graphic on the PFD indicative of the first estimated altitude, and (ii) a visual alert on the PFD when the difference between the first estimated altitude and the second estimated altitude exceeds a predetermined error threshold.

Abstract: Systems and methods for managing a visual display in a ground proximity warning system. In one embodiment, a system includes at least one aircraft sensor system operable to acquire aircraft data and a ground proximity warning computer coupled to the aircraft sensor system that is operable to process the aircraft data to generate ground proximity warning data corresponding to a sensed ground obstruction. An indicating system includes at least one visual display device that is operable to display terrain elevations and to display a visual symbol corresponding to at least one of the ground obstructions, wherein at least one of the computer and the visual display device is controllable to selectively alter an appearance of the visual symbol relative to the terrain elevations.

Abstract: This simplified self powered aircraft attitude survival indicator is easily and readily transportable from one aircraft to another and provides a simple indicator which gives a visual indication of aircraft attitude and alarms when the aircraft is in a dangerous attitude. The aircraft attitude indicator includes a housing containing a power source, multiple attitude sensors, and at least one piezoelectric alarm, and a front panel display with an arrangement of light emitting elements (electric bulbs or LEDs) providing visual attitude indicators.

Abstract: A display screen for displaying multiple sets of information is provided. The display screen includes at least one region of a select color designated to convey a first set of information and a plurality of adjustable areas designated to convey a second set of information. The plurality of adjustable areas overlay at least a portion of the at least one region of select color of the first set of information. Moreover, each adjustable area is defined by an outline and a color encased in the outline.

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: In a method of the invention for assisting the piloting of an aircraft, a guard curve (CGS) is determined as a function of the resources of the aircraft, the position of an obstacle (O) or a terrain point situated in front of the aircraft is measured by telemetry, the distance D between the guard curve and the obstacle (O) or the terrain point is calculated, and a pull-down order or a pull-up order is produced as a function of the distance D.

Abstract: An auditory attitude indicator for aircraft that includes an audio source providing an audible signal, a? stereo headset with a left side and a right side, an aircraft avionics system that provides at least aircraft pitch data and roll data to an audio processor unit. The audio processor unit includes at least one lookup table of coefficients corresponding to a plurality of possible aircraft pitch and roll orientations and at least two selectable multipoint finite impulse response filters. The first selectable multipoint finite impulse response filter having a first coefficient selected by the audio processing unit from the lookup table based upon the aircraft pitch data and roll data for varying the audible signal to the stereo headset left side. The second selectable multipoint impulse response filter for varying the audible signal to the stereo headset right side having a second coefficient selected by the audio processing unit from the lookup table based upon the aircraft pitch data and roll data.

Abstract: The present invention relates to a system for detecting deviation from a normal flight regime. The system includes at least one aircraft information system located on an aircraft for detecting an aircraft condition variable, a processing system configured to determine whether the aircraft condition variable is within a predefined tolerance of a predefined normal status for that aircraft condition variable, the processing system including an output device configured to transmit a signal indicative of a deviation from the predefined normal status, and a communication system for communicating between the aircraft and an external receiving station.

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 and a system are recited for obtaining a true azimuth heading for correcting a coarse azimuth heading measured from an observation position to a specific selected target by operating a data acquisition system disposed at the observation position. In principle, data is acquired and measurements are taken to allow calculation of a calculated target, including error area limits. The calculated target surrounded by error area limits is presented as a search zone to an operator for searching, finding and indicating on a display, on which is superimposed at least one map, of the specific selected target. Once found, calculations of the true azimuth are performed, allowing the derivation of the true North. The method and a system are operative with a variety of maps, including digital terrain models and stellar maps.

Abstract: A display screen for displaying multiple sets of information is provided. In one embodiment, an aviation display screen includes a main window and a plurality of miniature windows. The main window is adapted to illustrate one set of information. Each miniature window is adapted to display a set of avionic information. The avionic display is further adapted to toggle a select set of avionic information in one of the miniature windows into the main window.

Abstract: A system and methods for managing a visual display in a ground proximity warning system is disclosed. In one embodiment, a system includes at least one aircraft sensor system operable to acquire aircraft data and a ground proximity warning computer coupled to the aircraft sensor system that is operable to process the aircraft data to generate ground proximity warning data corresponding to a sensed ground obstruction. An indicating system including at least one visual display device that is configured to display an image of a visual symbol corresponding to the sensed ground obstruction is coupled to the computer. At least one of the computer and the visual display device is controllable to selectively alter an appearance of the visual symbol on the display.

Abstract: A system and method for filtering various targets (such as ground vehicles, stationary objects, and aircraft) from display on a display screen within the cockpit of an “Own Ship” aircraft. The system and method withhold from display any non-exempt targets that have an altitude that is either: (1) greater than an upper-threshold altitude; or (2) less than a lower-threshold altitude. The upper-threshold altitude and the lower-threshold altitude may be set to user-specified, customized values as desired to accommodate current flying conditions. In addition, the system and method may also be configured to operate in a plurality of operating modes, each of which features a different upper threshold altitude/lower threshold altitude combination. The system and method are preferably configured to reset certain threshold altitudes to pre-defined default altitudes in response to the aircraft landing.

Abstract: A wireless communication interface for inertial measurement unit is disclosed. One or more instrumentation sensors, a processor, a wireless radio frequency transceiver with an antenna, and a power source are sealed within an inertial sensor assembly. The processor is adapted to receive output signals from the instrumentation sensors and to convert the output signals into a stream of digital data packets. A radio frequency transceiver is coupled to the processor and adapted to wirelessly communicate the stream of digital data packets through the antenna. In one embodiment, the radio frequency transceiver is further adapted to wirelessly receive a stream of digital data packets through the antenna and communicate the received digital data packets to the processor.

Abstract: The invention concerns a method and a system for calculating a flight route between a first position and a second position. According to the method, the first position is chosen as the current position, and the following steps are then repeated until the second position is reached: a loss function is determined corresponding to each flight path in a set of flight paths that are predefined in relation to the current direction of flight; a flight path that yields the most advantageous value for the loss function is selected; a subsection from the current position and a predetermined number of positions forward are registered for the selected flight path, and the position at the end of the subsection is chosen as the new current position.

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: An improved system and method for eliminating terrain color confusion in aircraft displays are disclosed. An aircraft display system is described that includes a database for storing terrain data, a processing unit, an altitude determination unit, and a visual display. As the aircraft proceeds along a flight path, the processing unit determines the aircraft's current position and compares associated terrain elevation data stored in the database with altitude data received from the altitude determination unit. For example, if the processing unit's comparison of the stored terrain data and altitude data indicates that relative terrain data need not be displayed, then the processing unit provides absolute terrain color renderings to the display.

Abstract: A method for implementing a weather alarm in an outdoor computer includes defining atmospheric-pressure data repeatedly, defining altitude data repeatedly and essentially simultaneously with the atmospheric-pressure data, with the aid of a satellite positioning system, and converting both measured variables into the same measurement unit, either pressure or altitude. The difference between the converted variables is determined and is stored as a reference value, the difference between the converted variables is repeatedly monitored, and when the difference changes by more than a preset limit-value relative to the reference value, a weather alarm is given. Also an apparatus for performing the method.

Abstract: Systems and methods for controlling activation of a look-ahead function of a terrain alert and warning system. The system receives rate of climb and aircraft speed information, compares the rate of climb and aircraft speed information to a predefined threshold, and deactivates a look-ahead function based on the comparison.

Abstract: A method (200) is disclosed for designing an RNP approach for an aircraft at a particular runway (90). The method includes selecting a runway (201), gathering obstacle data for the obstacle evaluation area (202), selecting a VEB method and terms (204), laying out a preliminary approach, inducing a missed approach segment (206), calculating a preliminary obstacle clearance surface (208), calculating a momentary descent segment using a physical model of the aircraft (210), adjusting the obstacle clearance surface so that no obstacles intersect the surface (212), and optionally optimizing the approach by departing from the operator's standard procedures (214). Preferably, the obstacle clearance surface is adjusted so that it just touches an obstacle, without any object intersecting the surface, thereby providing an optimal decision altitude.

Abstract: A method (300) for extracting a digital elevation model from a plurality of raw topographical points representing a plurality of frames representing a plurality of perspectives of a multi-dimensional object comprising a surface and above-surface obstructions, comprises steps or acts of: finding the surface (304) by filtering out data points produced by the above-surface obstructions to provide a plurality of surface data points representing the surface; and filtering the surface data points (306) with a competitive filter to provide a multi-dimensional surface shell of digital elevation model data points. The above-described method can also be carried out by a specialized or programmable information processing system (200) or as a set of instructions in a computer-readable medium such as a CD ROM or DVD or the like.

Abstract: An aircraft terrain avoidance method and device may employ a collision warning section that transmits a caution signal when the aircraft risks colliding with the terrain at the end of a first predetermined period of time. A warning signal is transmitted when the aircraft risks colliding with the terrain at the end of a second predetermined period of time, which is shorter than the first predetermined period of time. A piloting system causes the aircraft to automatically climb with a first gradient corresponding to a predetermined value upon the transmission of the caution signal. An automatic pilot is engaged automatically, if currently disengaged, to force the aircraft to climb with a second gradient, corresponding to the maximum gradient possible in the current flight conditions of the aircraft, upon the transmission of the warning signal.

Abstract: The present invention is directed to a system and method for a safe flight display through increasing situation awareness by an optimal presentation, given limited capacity of the system. The system may determine which terrain area needs a detail representation and which area needs a coarse representation. A view-dependent visual error metric may be utilized to define and maintain an error bound and accurately minimize the amount of terrain data being depicted. By performing a breadth-first search on the terrain database, a user can determine amount of geometry to be displayed with limited bandwidth of data presentation. The user may be allowed to scale the application to his/her desired level of detail, given a capacity of the system. Therefore, the system may provide a safe flight display with an anticipated and graceful (all portions of the screen would be given an equal quality representation) degradation in performance upon the choice of the user.

Abstract: A method of removing synthetic vision terrain and objects from a graphical display when unsafe to rely on the synthetic vision terrain and objects is provided. The method comprises receiving current position data from at least one sensor, determining when to fade out synthetic vision terrain and objects based on the position data received, and fading out synthetic vision terrain and objects gradually when determined.

Abstract: A method for displaying attitude, heading, and navigation data on a single display is described. The method comprises configuring the display with terrain data, overlaying the terrain display with a compass rose display, and superimposing an attitude direction indicator with the compass rose display, the attitude direction indicator referenced to a center of the compass rose.

Abstract: A method and device for determines a safe altitude for an aircraft. The device includes a unit that determines a clear zone corresponding to a lateral area dependent on the flight of the aircraft. A unit determines the highest altitude of the ground that is located under this clear zone. A unit determines a safe altitude, by calculating the sum of the aformentioned highest altitude and a guard height.

Abstract: The present invention includes a system, method and computer program product for reducing nuisance warnings during low altitude flight conditions and in the presence of low position uncertainty. The system includes a first component that determines whether the aircraft is in a low altitude flight condition and a second component that determines the position, positional uncertainty, and the heading. The system also includes a third component that attenuates and refines the look-ahead envelope in accord with the determined condition of flight and positional uncertainty.

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: The invention relates to a method of synthesizing a cartographic image consisting of pixels and representing a terrain overflown by an aircraft, the cartographic image being computed at each pixel on the basis of several cues which include a first color altimetric cue obtained on the basis of a datum of absolute altitude or relative altitude with respect to the altitude of the aircraft, of a possible cue of presence of at least one intervisibility zone and of a possible cue of presence of a forest zone, a second shading cue representative of the relief of the terrain, and a possible third color planimetric cue, the entire set of altimetric cues constituting an altimetric image and the entire set of planimetric cues constituting a planimetric image, the method comprising at least two types of mode, on the one hand a normal mode type in which, at each pixel, the shading cue modulates the altimetric cue but not the planimetric cue and on the other hand an inverted mode type in which, at each pixel, the shading c

Abstract: A system, method and display for monitoring the performance of an aircraft during the take-off maneuver that includes the steps of monitoring the progress of the take-off maneuver by acquiring data representative of the aircraft's motion at a plurality of points during the maneuver, generating a function that best fits the acquired data, and using the generated function to predict future progress of the maneuver.

Abstract: A method for flying in a degraded visual environment comprising the steps of collecting environmental data, processing the data and fusing the data together into a combined input output. The output is fed into a head down display, head mounted or heads up display and, preferably to a fly-by-wire vertical take-off and landing capable vehicle wherein the fly-by-wire system makes automatic adjustments to the helicopter.

Abstract: A display control device, having a processor structured for receiving terrain elevation information and samples of current position and altitude above ground data; and one or more algorithms resident on the processor for generating, as a function of the current position and altitude above ground data, one or more display control signals for causing a display device to display, in a monochromatic scale graduated as a function of terrain elevation relative to mean sea level, a strategic portion of the terrain elevation information extending between a minimum elevation of the strategic portion of the terrain elevation information and a pre-selected strategic altitude threshold less than the altitude above ground data.