Abstract: Systems and methods are disclosed for identifying traffic to follow, TTF, on a display device. TTF, identification data identifying a vehicle to follow is received. Transmitted data is received from the vehicle to follow. Aircraft attribute data for the vehicle to follow is derived at least from the transmitted data and from target model data from a target model database. The aircraft attribute data includes position, orientation and aircraft dimensions. Enhanced vision system, EVS, imaging data is received from at least one EVS camera. An area of the EVS imaging data to be visually distinguished to highlight the traffic to follow is calculated. The area calculated is based on the aircraft attribute data including position, orientation and aircraft dimensions. Image processing is performed on the area of the EVS imaging data to visually distinguish the area so as to highlight the vehicle to follow, thereby providing highlighted EVS imaging data.

Abstract: A method for managing the display of an aircraft flight profile may be carried out by an electronic management device intended to be connected to a set of at least one terrain data base. Each terrain data base may have a respective resolution. The method may include selecting at least one resolution, as well as the terrain data base associated with each selected resolution. The method may further include generating data for displaying the flight profile and using each terrain data base selected. The method may also include where each resolution is selected according to a width of a corridor associated with a respective portion of the flight profile.

Abstract: A method of characterizing an aerosol, the method comprising illuminating aerosol particles located within a measurement volume with a first electromagnetic radiation pulse emitted from a first source and receiving one or more electromagnetic radiation returns that have been scattered by the aerosol particles illuminated by the first electromagnetic radiation pulse at one or more sensors, illuminating the aerosol particles within the measurement volume with a second electromagnetic radiation pulse emitted from a second source and receiving a one or more electromagnetic radiation returns scattered by the aerosol particles illuminated by the second electromagnetic radiation pulse at the one or more sensors, determine at least one of intensity based on the one or more electromagnetic radiation returns, and determine an aerosol parameter based on an algorithm and the at least one intensity.

Abstract: Improved systems and methods for dynamic readouts on a primary flight display are provided. The system includes a computer system configured to receive and process aircraft status data and flight plan data to command a display system to overlay on the image, (i) an analog indicator of the airspeed, (ii) an analog indicator of altitude, (iii) a digital airspeed indicator, and (iv) a digital altitude indicator. The system continuously determines whether steady flight conditions are occurring. Steady flight conditions include one or both of: constant airspeed and constant rate of change of airspeed. When the steady flight conditions are occurring, (i) and (ii) are removed from the image. When the steady flight conditions are no longer occurring, (i) and (ii) again overlaid on the image.

Abstract: A self-propelled device determines an orientation for its movement based on a pre-determined reference frame. A controller device is operable by a user to control the self-propelled device. The controller device includes a user interface for controlling at least a direction of movement of the self-propelled device. The self-propelled device is configured to signal the controller device information that indicates the orientation of the self-propelled device. The controller device is configured to orient the user interface, based on the information signaled from the self-propelled device, to reflect the orientation of the self-propelled device.

Abstract: Fault-tolerant liquid crystal displays are delineated for avionics systems. At least some example embodiments are methods including providing an avionics display full screen on the LCD, the providing being implemented by driving source signal lines of the LCD by way of a first source driver circuit through a first set of FETs; driving gate signal lines of the LCD by way of a first gate driver circuit through a second set of FETs; preventing back biasing of a second source driver circuit by electrically isolating the source signal lines from the second source driver circuit; and preventing back biasing of a second gate driver circuit by electrically isolating the gate signal lines from the second gate driver circuit.

Abstract: The disclosed methods include generating a navigation presentation for a device navigating a route. A virtual camera modifies how it captures map portions to produce scenes in the navigation presentation based on changes in navigation context. The method identifies different attributes describing different navigation contexts at different times during the navigation presentation, and uses these attributes to identify styles for operating the virtual camera. The method uses a style to specify the camera's positional attributes which define map portions that the virtual camera identifies for rendering to produce navigation scenes for some time (until the navigation context changes, or the presentation ends when the context does not change again). When the navigation context changes, the identified attributes may change. This change may cause selecting a new virtual camera style. When the style changes, the method modifies the way the virtual camera captures the portion of the map to render.

Abstract: A matched array technology system and method for displaying in a two-dimensional array the structured interaction between airspeed and angle of attack of an aircraft during various stages of flight. Proxy values of airspeed and angle of attack are defined and scaled so the axes of the array contain corresponding indicators resulting in a “matched array” and an embedded, unique “alignment vector” of cells where the underlying airspeed and angle of attack combinations are consistent with controlled flight. Wherever the proxy values intersect, indicators depict proximity to the alignment vector, and the direction and extent of adjustments to either or both airspeed and angle of attack needed to achieve and maintain controlled flight.

Abstract: An imaging system for a vehicle is disclosed. The imaging system comprises an imager configured to capture image data in a forward directed field of view relative the vehicle and an inertial sensor configured to measure a bank angle of the vehicle. A controller is in communication with the imager and the inertial sensor. The controller is configured to receive the image data comprising an imaging area and process the image data with enhanced sensitivity in at least one processing window within the imaging area. The controller is further configured to adjust a location of the processing window within the imaging area based on the bank angle and detect an object in the processing window.

Abstract: A radar system and method of detecting an object involve a first node including a first transmitter and a first receiver, and a second node including a second transmitter and a second receiver. The second receiver receives a first received signal from an object from a first transmission by the first transmitter, the first received signal including first phase noise with a first delay, and the first receiver receives a second received signal from the object from a second transmission by the second transmitter, the second received signal including second phase noise with a second delay. A processor processes the first transmission, the first received signal, the second transmission, and the second received signal to eliminate the inter-node phase noise and to estimate a location of the object relative to the radar system based on the first delay and the second delay.

Abstract: A vehicle attitude display such as a Primary Flight Display presents pitch and bank information by displaying a vehicle avatar as fixed, with respect to a moving artificial horizon while displaying a movable symbol at a position along the vehicle avatar that is proportional to the symmetry of the vehicle. Parts of the display are dynamically emphasized or de-emphasized to support rapid assimilation of key data. Display format may be dynamically adjusted depending on vehicle use conditions. Display is intended for use both in-vehicle, and remotely.

Abstract: A method for managing a symbology in an on-board viewing system for an aircraft, the graphical representation comprising the piloting and navigation symbology overlaid on a representation of the exterior landscape, the symbology comprises a first angular attitude scale comprising a first symbol called an aircraft mockup, a second speed scale, a third altitude scale and a second symbol called the speed vector. When the angular lateral distance between the position of the first symbol and the position of the second symbol is such that the second symbol is not overlaid on the lateral scales, the various scales are represented in the nominal position; when the angular lateral distance between the position of the first symbol and the position of the second symbol is such that the second symbol is overlaid on one of the scales, the various scales move and/or their size decreases.

Abstract: Automated throttle control is described herein. One disclosed example method includes calculating, using a processor, a thrust resolver angle based on a flight condition of an aircraft, and controlling a throttle from moving past at least one of the thrust resolver angle or a range defined by the thrust resolver angle to maintain the aircraft in a preferred flight mode.

Abstract: A method for displaying an attitude of an aircraft includes receiving a roll angle, a pitch angle and a yaw angle of the aircraft, generating a display image indicating the roll angle, the pitch angle and the yaw angle, and displaying the display image on a display device. The display image includes a spherical shell with a track angle scale projected onto the spherical shell along a latitude line of the spherical shell and with a pitch angle scale projected onto the spherical shell along a longitude line of the spherical shell. Furthermore, the display image includes a graphical aircraft attitude indicator inside the spherical shell rotated with respect to the spherical shell such that the graphical aircraft attitude indicator indicates the roll angle, the pitch angle and the yaw angle of the aircraft with respect to the spherical shell.

Abstract: Automated throttle control is described herein. One disclosed example method includes calculating, using a processor, a thrust resolver angle based on a flight condition of an aircraft, and controlling a throttle from moving past at least one of the thrust resolver angle or a range defined by the thrust resolver angle to maintain the aircraft in a preferred flight mode.

Abstract: In a method of controlling an interior lighting (25) in a vehicle (18), having a plurality of separately drivable lamps (26a-26g), provision is made that a motion light pattern, in particular a wave light pattern, is generated as a function of vehicle operating data by separately driving the individual lamps (26a-26g), the vehicle operating data including ambient data picked up by means of a light sensor.

Abstract: Systems and methods are described here to provide a degree or level of certification to a resident application such as an operating system, e.g., Linux®. In a Linux® implementation, the operating system provides a robust environment including many seasoned communication stacks, e.g., TCP/IP, USB, and the like. However, Linux® is not certified to the level necessary to be a part of many avionics applications. To eliminate the need to certify all of such an operating system, such certification being highly costly, the avionics application itself may be protected so that the operating system cannot alter the application's operating environment, e.g., application code and data, once the application is loaded and running. In this case, only the application requires certification at the highest level, and not the operating system such as Linux®.

Abstract: A wearable electronic device utilizes indicators on a display screen, such as tick marks positioned around the perimeter of the display, to point to the bearing of a desired location such as a nearest airport when GPS is enabled. The electronic device may be implemented as an aviation watch that comprises a display device having a screen including a plurality of indicators arranged proximal to a perimeter of the screen. The aviation watch determines a direction of an airport that is nearest in proximity to the location of the aviation watch and activates a subset of the plurality of indicators of the screen, the subset of the plurality of indicators providing a directional bearing to the airport determined to be nearest in proximity to the location of the aviation watch.

Abstract: An modular reflector assembly may include a shell and a support frame. The modular reflector assembly may also include a plurality of support links that mechanically couple the shell to the support frame. The shell may be thermally decoupled from the support frame by the plurality of support links.

Abstract: Systems and aircraft are provided. The systems and aircraft include a controller, a projection surface, and at least one pair of active shutter 3-D glasses. The 3-D projector is configured to project a first 3-D HUD layout onto a projection surface. The projection surface is configured for displaying the 3-D HUD layout. The controller is operatively coupled with the 3-D projector and is configured to control the projector to project the 3-D HUD layout onto the projection surface. The first pair of active shutter 3-D glasses is configured to synchronize with the 3-D projector to present the first 3-D HUD layout to a first user.

Abstract: Embodiments relate to a speed sensor and a speed sensing method for measuring relative speeds of receivers with respect to particles in a fluid by detecting individual particles. A receiver generates a plurality of signals related to reflections from particles in a region being monitored. A sampling circuit samples the signals, and a processing device processes the signals according to a particle detection scheme to determine speed. Concomitant use of the same receivers allows depth measurement.

Abstract: A system and method for providing sensor-based navigation correction of a GPS-sensed position of an aircraft includes a synthetic vision system. The synthetic vision system captures a visual image of the surrounding area via image sensors and generates a location model based on the image. A georeference engine compares the location model to static high-resolution terrain and obstacle databases to determine a corrected position of the aircraft. The georeference engine then updates the GPS-sensed position with the corrected position, transmitting the corrected position to the combiner. The combiner generates for display an enhanced image based on the visual image and the corrected position of the aircraft.

Abstract: A wearable electronic device utilizes indicators on a display screen, such as tick marks positioned around the perimeter of the display, to point to the bearing of a desired location such as a nearest airport when GPS is enabled. The electronic device may be implemented as an aviation watch that comprises a display device having a screen including a plurality of indicators arranged proximal to a perimeter of the screen. The aviation watch determines a direction of an airport that is nearest in proximity to the location of the aviation watch and activates a subset of the plurality of indicators of the screen, the subset of the plurality of indicators providing a directional bearing to the airport determined to be nearest in proximity to the location of the aviation watch.

Abstract: A system for rigging a control surface of an aircraft, wherein the control surface is movable relative to a reference structure of the aircraft by means of at least one actuator, comprises a mobile control unit having being connectable to at least one actuator, an input means for commanding a deflection of the control surface, and an optical rigging apparatus having a first rigging component and a second rigging component. The first rigging component is adapted for being mounted on a reference structure to which the control surface is swivably attached and the second rigging component is adapted for being mounted on the control surface itself. Thereby an accurate rigging may be conducted with a clearly reduced number of personnel and a clearly reduced time for completion.

Abstract: A dynamic runway indicator is displayed overlying a conformal runway for assisting a pilot in completing an approach to landing on a runway. The dynamic runway indicator includes a polygon, that by changing position with respect to the conformal runway, provides advanced instrumentation cues to the pilot for adjusting the aircraft flight path to a normal, or recommended, path to the runway for landing, thereby assisting the pilot to improve the accuracy and safety of the approach and landing.

Abstract: A method for controlling the piloting of an aircraft comprising the steps of receiving at least one first instruction for modification of a current velocity vector of the aircraft, determining a target velocity vector of the aircraft, on the basis of said at least one first instruction received, and determining, on the basis at least of said target velocity vector, at least one actuation command intended for at least one actuator of the aircraft in order to modify the movement of the aircraft according to said at least one first instruction received.

Abstract: According to the invention, a terrain avoidance maneuver is engaged when the alerts of a given pair of alerts are emitted simultaneously, the triggering of one of the alerts depending on the information provided by a first measurement chain and the triggering of the other alert of the pair relying on information provided by a second measurement chain, distinct from and independent of the first chain.

Abstract: The invention relates to an alarm apparatus (1) for a pilot's headset (3) and to a pilot's headset having such an alarm apparatus. The alarm apparatus comprises an attitude sensor (11), which detects its inclination relative to a starting position or the horizontal, and a measuring device (12) for recording a period for which the inclination recorded by the attitude sensor exceeds a stipulated inclination tolerance limit. In addition, the alarm apparatus has a means (13) which is set up to trigger an alarm signal when a recorded period of the inclination tolerance limit being exceeded is longer than a preset maximum period.

Abstract: A present novel and non-trivial system, apparatus, and method is disclosed for presenting a flight director-dependent highway in the sky (“HITS”) pathway on an aircraft display unit. A processor receives flight plan data and flight director data, generates HITS data set representative of a flight director-dependent HITS pathway using flight plan data and flight director data, and provides the HITS data set to a display system for presentation of the flight director-dependent HITS pathway on a tactical display unit. Flight plan data provided to the processor may comprise of data sourced by a navigation system or HITS pathway data generated independently of flight director data. When presented on a tactical display unit, the flight director-dependent HITS pathway may be depicted with the flight director, where the proximal end of the HITS pathway aligns with the flight director.

Abstract: A method of designating and communicating a desired LZ to an aircraft includes outputting a coded laser signal at or near a desired landing zone to indicate a location of the desired landing zone. The coded laser signal is received by an aircraft that desires to land at the desired landing zone. The location of the desired landing zone and an ingress path from a current location of the aircraft to the desired landing zone are determined by a processor provided with the aircraft.

Abstract: There is described an aircraft, comprising a windscreen arranged in a front side of aircraft, characterized in that an edge of windscreen defines a visualization area visible by an operator, and by comprising displaying means configured for displaying at least one visual information of at least one flight parameter within visualization area, at least when aircraft is in a normal flight configuration.

Abstract: One embodiment of the present invention includes an aircraft instrumentation system for a cockpit instrument panel having a first device associated with a first pilot of an aircraft and positioned on the instrument panel substantially in front of the first pilot. The first device may include a first display and a first controller, which may have a set of controls for controlling the first display and aircraft systems. The instrumentation system may also include a second device associated with a second pilot of the aircraft and positioned on the instrument panel substantially in front of the second pilot. The second device may include a second display and a second controller, which may have a set of controls for controlling the second display and the aircraft systems. The instrumentation may be configured such that at least one of the first display and the second display presents attitude, altitude and airspeed at all times.

Abstract: A composite normalized angle of attack indicating system provides a simultaneous display of both body angle of attack, such as in digital form, and normalized angle of attack for an aircraft. The display may be visually enhanced as stall is approached such as by zooming the body angle of attack digital display and/or by changing the color of the display. The normalized display also selectively displays an approach reference band when the flap setting is equal to or greater than 20 degrees.

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 system and method are provided for displaying terrain altitudes on an aircraft display that are easily understood by the pilot. A plurality of bands are defined, wherein each band defines a range of altitudes of terrain in the vicinity of the aircraft. A list of altitudes representing each band is displayed in a legend. A band is highlighted when a number associated therewith is selected, and a number is highlighted when the band associated therewith is selected. The band or number may be selected, for example, by cursor, or the band may be selected by position of the aircraft.

Abstract: Methods and systems are provided for improving pilot situational awareness during brown-over-brown display situations. An image is rendered, on a display, that includes one of, or both, rendered terrain and rendered sky. A sky veil is at least selectively rendered on a portion of the display. The sky veil, when rendered, is rendered at least partially transparent and in a manner that portions of the sky veil that overlap with rendered sky are not discernable, and rendered terrain is viewable through portions of the sky veil that overlap with terrain.

Abstract: Present novel and non-trivial system, device, and method for generating location information presented to a pilot are disclosed. A processing unit is configured to receive manual input data representative of one or more selected image location(s) on a first image data set; determine a selected geographic location for each selected image location; and update the second image data set to include location pointer data. As embodied herein, first and second images represented in the first and second image data sets, respectively, could be displayed simultaneously on the same display unit or separately on different display units. Also, the first image and second image could correspond to an egocentric view and a plan view, respectively, or vice-versa. Additionally, the first image data set and/or second image data set could be updated include first and/or second location pointer data, respectively.

Abstract: The display system (1) comprises means (5, 11A, 14) to take into account a recorded symbology, in the event of a malfunction in the emission of a symbology, to perform a display of symbology.

Abstract: In a centralized navigation information management system installed on board an aircraft which is in a current position at a current time, the aircraft having a warning management system and a route management system with means for creating a route plan, the route plan having a future route plan corresponding with the part of the route plan beginning at the current position and at the current time, the system includes: means for creating a task comprising at least one task parameter relating to an item of navigation information, including a task variable corresponding to a condition of execution of the said task, the means for creating a task having means for determining a predicted time meeting the execution condition; and means for detecting a possible inconsistency between the created task and the route plan or the future route plan and for transmitting, when an inconsistency is detected, a message relating to the inconsistency to a first display means of a centralized warning management system to display

Abstract: A system for displaying pitch- and power-based guidance commands and flight path information for a variety of display modes (climb, cruise, descent, landing) to pilots in response to situations wherein the measured air data should not be relied upon. This information is presented in an intuitive and expedient manner exactly when and where it is needed on the primary flight display. The displayed information dynamically changes in response to airplane parameters.

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: 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: The present invention relates to a system (1) and an associated method for managing audio warning messages in an aircraft. The system (1) comprises a plurality of monitoring systems (10, 20) capable of detecting the establishment of at least one warning condition (CA), and comprises a central broadcasting module (40), to which each of the monitoring systems is connected and which is capable of broadcasting an audio message (SIG) corresponding to a detected warning condition. In particular, in this system (1), the said central broadcasting module (40) comprises means (402, 420) for determining at least one priority warning condition among the warning conditions detected by the monitoring systems, and means (410, 430) for generating at least one audio message (SIG) corresponding to the at least one determined priority warning condition, in order to broadcast it.

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

Abstract: This aircraft control cabin comprises an avionics display device with multiple fixed screens (10a-10d) and at least one screen (15, 16) as an accessory, designed to be a replacement screen or extra screen for the avionics display system. The screen (15, 16) is a touch screen housed in a retractable tablet which slides underneath an instrument panel in the control cabin, the touch screen (15, 16) being designed to occupy a stowed position underneath the instrument panel, a first position of use in the retractable tablet in which the touch screen (15, 16) acts as a means of interaction for controlling various items in the control cabin and a second position of use in which the touch screen (15, 16) is put in a position in which it replaces or supplements a screen (10a-10d) belonging to the avionics display system. Use in an aircraft.

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

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

Abstract: The invention relates to an alarm apparatus (1) for a pilot's headset (3) and to a pilot's headset having such an alarm apparatus. The alarm apparatus comprises an attitude sensor (11), which detects its inclination relative to a starting position or the horizontal, and a measuring device (12) for recording a period for which the inclination recorded by the attitude sensor exceeds a stipulated inclination tolerance limit. In addition, the alarm apparatus has a means (13) which is set up to trigger an alarm signal when a recorded period of the inclination tolerance limit being exceeded is longer than a preset maximum period.

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 approach is provided for an augmented reality user interface. An image representing a physical environment is received. Data relating to a horizon within the physical environment is retrieved. A section of the image to overlay location information based on the horizon data is determined. Presenting of the location information within the determined section to a user equipment is initiated.