Abstract: Disclosed is a compact, multi-user magnetic tracking system. In an embodiment, a compactness is achieved by using a single coil and inertial sensors at the transmitter and magnetometers and inertial sensors at the receiver for sensing the magnetic field generated by the single coil and for determining a position and attitude of the receiver relative to the transmitter. The transmitter and receiver each include a wireless transceiver for exchanging clock synchronization data and sending transmitter attitude data to the receiver. In another embodiment, frequency or time division multiplexing is used to differentiate between multiple users of the multi-user magnetic tracking system.

Abstract: A method for determining an attenuation of a wind caused by a simulated obstacle and experienced by a simulated vehicle in a simulation, comprising: receiving a wind direction and an initial speed for a simulated wind; generating a line of sight vector having a source position, a given direction and a given length, the given direction being one of opposite to the wind direction and identical to the wind direction; determining a distance between the simulated obstacle and the simulated vehicle using the line of sight vector, the distance being at most equal to the given length of the line of sight vector; determining a wind attenuation gain using the distance between the simulated obstacle and the simulated vehicle; determining an actual speed for the simulated wind using the initial speed of the simulated wind and the gain for the wind attenuation; and outputting the actual speed.

Abstract: The invention relates to a communication network for an aircraft comprising at least one processing member and a first switch which is connected to the first processing member in order to provide data exchange within the first processing member and/or between the first processing member and at least one user terminal remote from the first processing member and connected to the first switch. According to the invention, the first switch comprises local means for observing logical communication channels of the first switch, and the first processing member includes means for controlling said observation means.

Abstract: A method for providing task management assistance in managing the flight path to the flight crew is provided.

Abstract: A cockpit pressurization and oxygen warning system includes a cabin pressure input and an aircraft pressure input. A pilot interface includes a first visual indicator having a first recognizable characteristic disposed in a first position that is made visually perceptible when a first signal is asserted and a second visual indicator having a second recognizable characteristic esthetically different from the first recognizable characteristic and disposed in a second position different from the first position that is made visually perceptible when a second signal is asserted. A control circuit that is responsive to the cabin pressure input and the aircraft pressure input determines an acceptable range for the cabin altitude that corresponds to the aircraft altitude. The control circuit asserts the first signal when the cabin altitude is within the acceptable range and asserts the second signal when the cabin altitude is not within the acceptable range.

Abstract: A time-sensitive, data reduction system is described. According to an aspect of the system, a method is disclosed that comprises: receiving at least a portion of an airline-specific dataset, wherein the airline-specific dataset comprises a plurality of location records, wherein each location record comprises a point of interest (POI) and a unique rank, wherein the POI is defined by unique geographic identifier; determining a current position of the aircraft; and based on the current position and based on the unique rank of each of the plurality of location records, controlling, at a passenger display in the aircraft, a presentation of a map and a plurality of POI indicators associated with a highly-ranked subset of the plurality of location records. According to another aspect of the system, a plurality of servers are used provide relevant location-related content to an aircraft passenger.

Abstract: Embodiments include apparatus and methods for modeling air flow from flight responses in aerial vehicles. Sensor data is received for aerial vehicles in a geographic area. The pose (e.g., roll, pitch, and yaw) of the aerial vehicles is calculated from the sensor data. One or more wind vectors are calculated based, at least in part, on the pose. An air flow model is generated from the wind vectors.

Abstract: A method for displaying obstacle detection for an unmanned aerial vehicle (UAV) includes receiving obstacle information associated with at least one direction of the UAV. The obstacle information is obtained by analyzing a sensing signal of at least one sensor of the UAV. The method further includes displaying the obstacle information.

Abstract: Embodiments of the present invention relate to a flight direction display method and apparatus, and an unmanned aerial vehicle. The method includes: obtaining a flight direction indication of an aircraft sent by a camera system, where the flight direction indication is determined by the camera system according to a relative angle between a camera apparatus and the aircraft; and displaying the flight direction indication of the aircraft on a shooting preview screen. In this way, a flight direction of the aircraft is controlled according to the flight direction indication, so that in a shooting process, a flight direction of a fuselage of the aircraft is the same as a rotation direction of the camera apparatus, so as to shoot content wanted by the camera apparatus, thereby improving user experience.

Abstract: A flight information storage system for an airplane according to the present invention may include: one or more of a video acquiring device mounted on the airplane; a recording device for recording video acquired through the video acquiring device(s) during a flight of the airplane; and a travel storage device which simultaneously stores the video data recorded by the recording device. Here, the travel storage device may be a USB cartridge, and the video acquiring device may be one or both of a digital camera and a radar device. The digital camera may include a first digital camera that is installed in front of the cockpit of the airplane to capture an image to the front of the airplane during flight, and two or more second digital cameras installed behind the cockpit of the airplane to capture an image of the instrument panel of the airplane and the area surrounding the instrument panel.

Abstract: Boundary information associated with a three-dimensional (3D) flying space is obtained, including a boundary of the 3D flying space. Location information associated with an aircraft is obtained, including a location of the aircraft. Information is presented based at least in part on the boundary information associated with the 3D flying space and the location information associated with the aircraft, including by presenting, in a display, the boundary of the 3D flying space and an avatar representing the aircraft at the location of the aircraft.

Abstract: Aircraft, computing devices, and Head-Up Displays (HUDs) are provided. An aircraft includes an avionics system with a display screen and a controller. The display screen is configured to present an image arrangement that is visible to a user. The controller is configured to generate curved tapes in the image arrangement to convey flight values to the user. The curved tapes are configured to direct an eye of the user to a portion of the image arrangement. The controller is further configured to roll the curved tapes three-dimensionally based on changes to flight values of the aircraft to provide peripheral indication of changes to flight values when the flight values are changing.

Abstract: The present invention relates to a method for displaying traffic in the vicinity of a reference aircraft in a non-compliant display zone, and comprising the following steps: acquisition (110) of a position of one of the surrounding aircraft and determination of a relative two-dimensional position of the surrounding aircraft relative to the reference aircraft in a real plane and at a relative altitude; associating (120) a traffic symbol with the surrounding aircraft; determination (130) of a two-dimensional position of the reference aircraft in a virtual plane representative of the real plane; displaying (140) in perspective the virtual plane and the traffic symbol at the distance of the two-dimensional position of the reference aircraft in this virtual plane.

Abstract: An apparatus for monitoring at least one performance characteristic of a component of a vehicle may include a tripod connected to an exterior surface of the vehicle, the tripod includes a plurality of airfoils defining an aerodynamic surface of the tripod, a camera positioned on the tripod at a predetermined viewing angle directed toward the component of the vehicle and a camera fairing connected to the tripod and surrounding the camera, the camera fairing includes a sidewall defining an aerodynamic surface of the camera fairing, an aperture disposed through the sidewall and aligned with the camera and a plurality of protrusions positioned proximate the aperture.

Abstract: The present disclosure is directed to autonomous control systems and methods for navigating an aircraft relative to a movable object. The autonomous control system may comprise: a first one or more sensors to track the movable object in a local coordinate frame; a second one or more sensors to track the aircraft in the local coordinate frame; and a flight control system having a processor that is operatively coupled with the first one or more sensors and the second one or more sensors, the flight control system configured to provide pitch, roll, and yaw commands to the aircraft. The processor may be configured to identify a perch point at a predetermined distance relative to the movable object in the local coordinate frame. The perch point may be fixed relative to the movable object. The processor may be configured to navigate, via the flight control system, the aircraft to the perch point as a function of the speed, the position, or the heading of the movable object.

Abstract: An aircraft system may include a civil radio, a mission radio, and an adaptive flight display. The adaptive flight display may include a display, a processor, and memory. The memory may maintain a civil radio tuning system application and a mission radio tuning system application. The civil radio tuning system application and the mission radio tuning system application may be associated with the civil radio and the mission radio, respectively. The processor may be configured to: execute the civil radio tuning system application and the mission radio tuning system application; tune the civil and mission radios; generate a graphical user interface multifunction window including slots; assign slots to display information associated with the civil and mission radio tuning system applications; and output, to the display, the graphical user interface multifunction window having particular slots filled with the information associated with the civil and mission radio tuning system applications.

Abstract: A cockpit pressurization and oxygen warning system includes a cabin pressure input and an aircraft pressure input. A pilot interface includes a first visual indicator having a first recognizable characteristic disposed in a first position that is made visually perceptible when a first signal is asserted and a second visual indicator having a second recognizable characteristic esthetically different from the first recognizable characteristic and disposed in a second position different from the first position that is made visually perceptible when a second signal is asserted. A control circuit that is responsive to the cabin pressure input and the aircraft pressure input determines an acceptable range for the cabin altitude that corresponds to the aircraft altitude. The control circuit asserts the first signal when the cabin altitude is within the acceptable range and asserts the second signal when the cabin altitude is not within the acceptable range.

Abstract: An assembly for implementing an aircraft trajectory includes a flight management system including a viewer, and a display application, on the viewer, for navigation data of the aircraft including waypoints of the aircraft along a trajectory. The flight management system includes an application for recovering tactical track monitoring data, the display application being able to display, dynamically on the viewer, a tactical track positioning symbol corresponding to the or each tactical track being monitored, the position of the positioning symbol being updated by the display application as a function of position data of the aircraft and tactical track monitoring data corresponding to the tactical track, received from a data acquisition apparatus, via a data transmission system.

Abstract: A system described herein includes a receiver component that receives a first graphical user interface of a first computer-executable application and a second graphical user interface of a second computer-executable application. The system also includes an integration component that automatically causes a portion of the first graphical user interface and a portion of the second graphical user interface to be simultaneously displayed on a display screen in an integrated graphical user interface that appears to an end user as being a single application.

Abstract: The general field of the invention is that of the methods for graphic representation of the relative position of the sky and of the earth in an onboard display system for aircraft, said graphic representation being displayed on a display screen comprising piloting and navigation information superimposed on a three-dimensional synthetic representation of the outside landscape. Said graphic representation is displayed only when the attitude of the aircraft is unusual, an unusual attitude corresponding to a roll value or to a pitch value located outside of a first range of nominal values. It comprises two disc segments of identical form, that are opaque and of different colour, situated symmetrically on a circle concentric to that bearing the roll scale, the straight-line segments of the two disc segments being parallel to the line representing the zero longitudinal trim indicator, the rotation of the two disc segments being slaved to the rotation of said zero longitudinal trim indicator.

Abstract: A method and system for use onboard an ownship, the method includes generating on a cockpit display an alignment symbol, track bug, and heading bug to aid to align a track angle and heading of the ownship with a runway course by a pilot; and enabling a pilot to view the alignment symbol, the track bug and the heading bug and to maneuver the ownship to maintain first, an alignment of the heading to the runway course and second, to attempt to align a track angle of the ownship with the runway course by adjustments made to maneuver the ownship in a course of landing by a view of a relative position of each of the alignment symbol, the track bug, and the heading bug to each other to serve as an indicator to the pilot of adjustments needed in the course of landing.

Abstract: Boundary information associated with a three-dimensional (3D) flying space is obtained, including a boundary of the 3D flying space. Location information associated with an aircraft is obtained, including a location of the aircraft. Information is presented based at least in part on the boundary information associated with the 3D flying space and the location information associated with the aircraft, including by presenting, in a display, the boundary of the 3D flying space and an avatar representing the aircraft at the location of the aircraft.

Abstract: A remote optical control surface indication system comprising mechanisms configured to engage heads of respective fasteners that attach an alignment indexing plate to a vehicular structure having a control surface coupled thereto. The system further comprises: a camera having a field of view that encompasses a portion of an end face of the control surface when the mechanisms are engaged with the fasteners and when the control surface is in a neutral position; a source of light that is activatable to project light that illuminates the end face of the control surface; a display screen comprising an array of pixels; and a computing system configured to process image data captured by the camera to determine a current position of a centerline of the end face of the control surface relative to a baseline position and control the display screen to display symbology indicating the current position relative to the baseline position.

Abstract: A flight range-restricting system is configured to control a flight range of an unmanned aerial vehicle (UAV). The flight range-restricting system includes a database including a UAV capabilities storage area that stores UAV capabilities data indicative of technical specifications of the UAV, and a restricted airspace storage area that stores restricted airspace data indicative of a restricted airspace. A range-restricting control unit is communicatively coupled to the database. The range-restricting control unit controls the flight range of the UAV based on a current location of the UAV, the UAV capabilities data, and the restricted airspace data.

Abstract: A processing apparatus includes a distance image acquirer, a moving-object detector, and a danger-level determining unit. The distance image acquirer acquires a distance image containing distance information of each pixel. The moving-object detector detects a moving object from the distance image. The danger-level determining unit determines a danger level of the moving object by use of the distance image, and outputs the danger level to a controller that controls a controlled unit in accordance with the danger level.

Abstract: A flight planning system for navigation of an aircraft utilizes a touch screen display device mounted in an aircraft cockpit spanning the width and height of the instrument panel. The system provides navigational views, an interactive map, charts, a radio frequency component, a weather component, and a virtual flight plan. A flight planning method uses an interactive map on a touch screen device in an aircraft cockpit. The method accepts user inputs and displays a desired flight plan on the map. A method for providing a chart on a touch screen device includes presenting a list of menu options on a touch screen mounted in an aircraft cockpit. The method provides the flight crew with heads-up operation, providing greater situational awareness.

Abstract: A configurable control panel for an aircraft cockpit includes a set of universal control modules each comprising at least one screen including at least one manually manipulable control key. Each of the control modules further includes at least one master control module, and at least one universal slave module associated with the master module, and including a screen and at least one control key. The at least one master module is configured to control the screen and the at least one control key of the at least one universal slave module.

Abstract: A method of monitoring a cockpit of an aircraft includes receiving, by one or more controllers, an image depicting an operator manipulated input device located within the cockpit. The method can include determining, by the one or more controllers, an observed state of the operator manipulated input device. In particular, the observed state can be based on the image. The method can include determining, by the one or more controllers, a sensed state of the operator manipulated input device. In particular, the sensed state can be based on data from a sensor. The method can include determining, by the one or more controllers, a mismatch between the observed and sensed states of the operator manipulated input device.

Abstract: Systems and methods for processing flight information. Using a flight plan/route message and other flight information (aircraft type and navigation database information), the portion of the message containing the flight plan or route is decoded and translated to construct a ground-based flight route comprising a list of waypoints and associated flight information. The list of waypoints may then used in calculations performed by a flight trajectory predictor to identify spatially associated weather information and/or to create an updated flight plan or route (e.g., by adding or changing waypoints in a flight object) and thereafter transmit that information to users. Prior to transmitting any updated flight plan/route, the associated waypoints and other flight information must be translated and encoded into the required format for inclusion in an outgoing (i.e., uplinked) flight plan/route message.

Abstract: A method for displaying an image to a pilot (20) of an aircraft (2). The method comprises, using a first value of the velocity of the aircraft (2) relative to a runway (4), displaying, on a HMD (24), an indication of a first position for an image component (e.g. a FPM) (36), the first position being the position, from the pilot's point of view, that the image component (36) would occupy if the aircraft (2) was established on a predefined glideslope (16); using a second value different to the first value, displaying, on the HMD (24), an indication of a second position for the image component (36), the second position being the position, from the pilot's point of view, that the image component (36) would occupy if the aircraft (2) was established on a different glideslope.

Abstract: A system, device, and method for generating and presenting navigation chart information are disclosed. The navigation chart information presenting system may include a display system comprised of one or more display units receiving image data set representative of an image of navigation chart information from an image generator (IG). The IG may be configured to acquire navigation chart data and generate the image data set as a function of the navigation chart data. The navigation chart data could be representative of a plurality of sections shown in a first visual format of a navigation chart, where each section of the plurality of sections is comprised of a plurality of feature names and feature information associated with one of the plurality of feature names. The image data set could be representative of a plurality of page images comprised of at least a portion of the navigation chart information.

Abstract: A method includes obtaining data associated with operation of a vehicle and determining a first operational phase of the vehicle based on the data. The method includes identifying a candidate operational phase transition from the first operational phase to a candidate operational phase based on a first portion of the data satisfying a first condition associated with the candidate operational phase, the first portion of the data associated with a first time. The method includes evaluating a second portion of the data based on a second condition associated with the candidate operational phase, the second portion of the data associated with a second time that is subsequent to the first time. The method further includes, based on the second condition being satisfied, generating an operational phase transition indication associated with the first time and that indicates an operational phase transition to the candidate operational phase.

Abstract: An improved aircraft display system and method that generates an aircraft orientation cue are provided. The aircraft orientation cue may be displayed in a variety of panoramic and landscape displays, and on head up and on head down display. The aircraft orientation cue has a symbolic form sufficient to visually convey, simultaneously, and in a predetermined manner, each of the AOA, roll, and yaw of the ownship A/C.

Abstract: A method and system for enhancing situational awareness in a rotary wing aircraft, includes receiving signals indicative of environmental information for the aircraft during a hover; determining signals indicative of a heading, course, and speed for the aircraft in response to the receiving of the environmental information; and displaying a composite symbology for heading, course, and speed on tactical display.

Abstract: A protection device including a unit for implementing a protection function that prevents the aircraft from flying under a given height with respect to the ground. The device includes a unit for determining the current values of parameters, and at least the current position of the aircraft and a current heading deviation of the aircraft with respect to a landing strip. A calculation unit is provided for calculating, during a landing on the landing strip, from data including said current values, a current longitudinal distance defined in the horizontal plane and necessary for bringing the aircraft into a position for deactivating the protection function. A checking unit is provided for checking whether a condition dependent on the current longitudinal distance is met, the protection function being automatically deactivated if the checking unit concludes that this condition is met.

Abstract: A system for an aircraft and method of determining intrusion of an avionics component or system in an aircraft having multiple avionics components and systems communicating over an aircraft communications network monitored by a system, including monitoring, by the system, data communication over the aircraft communications network for at least some of the avionics components or system and comparing, by the system, the monitored communications for the at least some of the avionics components to corresponding operational profiles.

Abstract: Systems and methods for training an operator. One system includes a computing device including a processing unit and computer-readable medium. The computer-readable medium stores a training simulator application. The training simulator application, when executed by the processing unit, is configured to (i) receive an operating command from the operator, (ii) generate a simulated working environment and a simulated shovel having a simulated dipper, the simulated shovel and the simulated dipper positioned within the simulated working environment based on the operating command, (iii) generate an indicator providing depth-related information to an operator relating to a position of the simulated dipper with respect to a point-of-reference within the simulated working environment, and (iv) output the simulated working environment and the indicator to at least one output device for display to the operator.

Abstract: Embodiments of the present invention provide a processing device implemented method of estimating journey attributes, comprising selecting a plurality of mobile device journey data according to on one or more criteria associated with end points of the mobile device journey data; determining virtual journey data based upon the plurality of mobile device journey data; determining one or more attributes of the virtual journey data. In some embodiments, the one or more criteria include a distal and/or temporal separation between the journey data.

Abstract: A system and method are disclosed for indicating to an aircrew of an aircraft an unstable approach to a desired landing. When the energy state of the aircraft exceeds a threshold, a suggested airspeed in consideration of the energy state is displayed. Additionally, a landing spots on a displayed runway are shown indicating where the aircraft would land in view of the energy state and where the aircraft is recommended to land in view of the current aircraft type and weight. A text message may also be displayed that conveys the ability of the aircraft to land.

Abstract: A display system for a vehicle includes a processing unit configured to receive data representative of flight path information and terrain and to supply display commands associated with the flight path information and the terrain; and a display device coupled the processing unit and configured to receive the display commands and operable to render a three-dimensional view, including symbology representing the flight path information on the terrain.

Abstract: Methods and apparatus are provided for selectively balancing pilot workload. The apparatus comprises a display device configured to display a user interface (UI) and a processor. The processor is configured to determine a state of the pilot and/or a state of the aircraft, prepare modification to the UI based in part on the state of the pilot and/or the state of the aircraft such that the modification adds one or more command icons without obscuring, without removing, and without replacing any information item on the display, and to execute the modification.

Abstract: Extended runway systems and methods include generating a runway centerline that extends from a start point on the runway to an endpoint located at a predefined distance from the start point. One or more distance markers are also calculated for the runway centerline. Display data is provided to an electronic display that causes the display to show the runway centerline and the one or more distance markers.

Abstract: Methods and systems for interfacing with multi-input devices employ various techniques for controlling the window framing of images. Such techniques provide control, including moving, sizing, and orientating, of one or more displayed window frames in which one or more images are displayed.

Abstract: The general field of the invention is that of display systems comprising means for generating graphic symbols and an associated semitransparent display device. The display device according to the invention has two overlaid semitransparent flat display screens, one passive and the other active, each symbol displayed on the semitransparent display device comprising a first representation and a second representation. The first representation is displayed on the first display screen with a low transmission rate for the light and with a predetermined first size. The second representation is displayed on the second display screen in the same place as the first representation, with a luminance and a predetermined second size that is smaller than the first size so that the second representation is overlaid on the first representation and the displayed symbol appears bright with a dark border.

Abstract: Rendering 3D paintings can be done by compositing brush strokes embedded in space. Image elements are rendered into an image representable by a pixel array wherein at least some of the image elements correspond to simulated painting strokes. A method may include determining stroke positions in a 3D space, determining stroke orders, and for each pixel to be addressed, determining a pixel color value by determining strokes intersections with a view ray for that pixel, determining a depth order and a stroke order for intersecting fragments, each fragment having a color, alpha value, depth, and stroke order, assigning an intermediate color to each of the fragments, corresponding to a compositing of nearby fragments in stroke order, and assigning a color to the pixel that corresponds to a compositing of the fragments using the intermediate colors assigned to the fragments. The compositing may be done in depth order.

Abstract: A display system and method are provided for an aircraft. The system includes a processing unit configured to determine a visual segment for the aircraft and to generate display commands based on the visual segment; and a display device coupled the processing unit and configured to receive the display commands and to display symbology representing the visual segment as a visual segment marker.

Abstract: A device for providing flight condition information and a method of displaying such information. In one form, the device functions as a backup system to provide flight condition information in the event of partial or complete inoperability of a primary flight instrument system, or to complement such primary flight instrument system. Numerous sensors collect flight data, which can pass through devices to convert and manipulate the data to produce flight condition information that can be displayed in such a way as to reduce a pilot's cognitive workload. The information displayed includes at least flight path angle, lateral acceleration, and turn rate. Additional information that may be displayed includes heading information, as well as information relating to airspeed and altitude, among others. In another form, the device can be part of either a primary or backup system.

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: A method is provided for displaying integrated minimum vectoring and safe altitude information on a display device in an aircraft. The method comprises displaying a graphical representation of a safe altitude sector and a vectoring altitude sector on the display device, and displaying a graphical representation of the aircraft on the display device to indicate the current location of the aircraft and a minimum altitude value associated therewith. The safe altitude sector corresponds to a first geographic area having a designated minimum safe altitude value associated therewith. The vectoring altitude sector corresponds to a second geographic area having a designated minimum vectoring altitude value associated therewith that is below the designated minimum safe altitude value. The graphical representation of the aircraft is displayed within at least one of the graphical representation of the safe altitude sector and the graphical representation of the vectoring altitude sector.

Abstract: A device for displaying flight characteristics of an aircraft is provided. The device includes a display for the selective display of flight characteristics of an aircraft, as a function of a state of credibility assigned to measurements from static pressure, total pressure and incidence sensors, configured for selectively displaying a primary set of flight characteristics comprising at least one flight characteristic coming from a measurement from one of said sensors, when the measurements from said sensors are deemed reliable, and a secondary set of flight characteristics, distinct from said primary set, comprising at least one secondary flight characteristic designed to replace a counterpart flight characteristic from the primary set, when the measurements from at least one sensor are deemed unreliable, said secondary flight characteristic being independent of any measurement by the or each sensor deemed unreliable done when the measurements from that sensor are deemed unreliable.