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: Methods and systems are provided for providing a runway awareness system for an aircrew of an aircraft. The method comprises receiving a first data stream that provides operational characteristics of a primary aviation parameter on approach to the runway. A second data stream is also received that provides operational characteristics of an alternative aviation parameter on approach to the runway. The first data stream and the second data stream are then displayed in a comparative layout format on a flight display for the aircrew of the aircraft during the approach to the runway.

Abstract: Example methods and systems for contingency landing a UAV are provided, comprising sensors configured to detect a position of the UAV and a command module. The command module receives a mission profile comprising a travel path mapped out in multidimensional space over time from an origin to a destination, a first boundary circumscribing at least a portion of the travel path, a second boundary circumscribing the first boundary, and contingent landing sites. The command module sends instructions to the UAV to fly according to the mission profile and determines a position of the UAV relative to the first and the second boundaries. Responsive to determining that the UAV is positioned at the first boundary, the command module sends instructions to land at a contingent landing site, and responsive to determining that the UAV is positioned at the second boundary, the command module sends instructions to land immediately.

Abstract: Methods and system for alerting a Visual Decent Point (VDP) in an aircraft system. The methods and systems retrieve runway altitude data and Minimum Descent Altitude (MDA) data from an avionics database for a target runway. Data in the avionics database for the target runway does not include a published VDP. The method includes calculating the VDP based on a difference between the runway altitude data and the MDA so as to achieve a target downward acceptable glidepath angle during final descent from the MDA to the target runway. The method includes outputting an alert of the VDP by an output device of the aircraft system.

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 method for guidance and for assisting in following a trajectory for velocity-vector piloting of an aircraft includes a step of calculating, at all times, lateral and vertical offsets of the current position of the aircraft from a target trajectory, estimated by a flight management system, and then a joining heading and a joining gradient for the aircraft to join the trajectory depending on these offsets; and a following fourth step of displaying, in head-up or head-down form, a consistent guidance symbol centered on the calculated joining heading and the calculated joining gradient for joining the trajectory, on a piloting screen showing a velocity vector. The fourth step may display, in addition to the guidance symbol, one or more items of information anticipating the next trajectory break.

Abstract: An aircraft angle of attack and sideslip angle indicator includes a display responsive to angle of attack and sideslip angle measurements from an angle of attack sensor and a sideslip angle sensor on an aircraft. The display depicts angle of attack along a first (preferably vertical) axis, and sideslip angle along a second (preferably horizontal) axis, with the axes intersecting at a display datum which represents acceptable angle of attack and sideslip angle values from the aircraft. The display depicts the aircraft's current angle of attack and sideslip angle with respect to the display datum, thereby indicating to the pilot whether non-optimal (and perhaps dangerous) flight conditions are occurring.

Abstract: A reconfigurable synoptic system utilizes commercial-off-the-shelf components to receive files indicating all of the connected avionics component and defining a weight of each component corresponding to the criticality of the component. The system divides the available display space into boxes that occupy space on the display based to the criticality of the corresponding component. Avionics components may be assemblages of sub-components, in which case the space designated for the component may be further divided according to its sub-components or the space designated for the component may be selectable to produce a similar display of only sub-components.

Abstract: Systems, methods, and devices are provided for generating flight restriction zones associated with flight response measures. The flight restriction zones may be generated with one or more flight restriction strips. Flight response measures for an unmanned aerial vehicle (UAV) may be directed based on a location and/or movement characteristic of the UAV relative to the one or more flight restriction strips. Different flight-response measures may be taken based on various parameters.

Abstract: Avionics systems, controllers, and aircraft are provided. An avionics system includes a display unit and a controller, and an aircraft includes the avionics system. The display unit is configured to present an image. The controller is communicatively coupled with the display unit and is configured to control the display unit to present the image in a takeoff mode and in a flight mode of the controller. The controller is further configured to receive signals indicating an aircraft attitude, a target attitude, and an aircraft flight path, to generate a marker in the image in the takeoff mode based on an attitude difference between the aircraft attitude and the target attitude, to generate the marker in the image in the flight mode based on the aircraft flight path, and to generate a signal that causes the display unit to present the image.

Abstract: A device is provided for assisting in the piloting of a vehicle, in particular an aircraft. The device includes a surface displaying images and a display management unit for images designed to be displayed on the display surface superimposed on a view of the outside landscape. The management unit is capable of commanding the display of piloting information images on the display surface. The management unit is capable of commanding the display, for at least one of the piloting information images, of an animation intended to attract a user's attention to that piloting information image, the animation comprising the display of an alert image and the shrinkage of the alert image.

Abstract: A vehicle system is provided. The system includes a processor configured to receive data representative of a current attitude and a desired attitude and to generate display signals associated with the current attitude and the desired attitude. The system further includes a display device configured to receive the display signals and operable to selectively render an image including roll angle alert symbology. The roll angle alert symbology includes a first curved arrow.

Abstract: An intuitive display including a visual representation of a maximum admissible angle of attack on a pitch scale giving the crew of an aircraft a visual recognition of an imminent stall, or of a stall, together with real assistance with piloting during the stall until the aircraft has come out of the stall completely.

Abstract: The disclosed embodiments relate to an aircraft that includes system for selecting an airspeed reference that is displayed within a cockpit of an aircraft. The system includes a processor and a display located in the cockpit. The processor is configured to determine whether primary airspeed is valid or invalid, and, to select a backup airspeed as the airspeed reference that is output to the display when it is determined that the primary airspeed is invalid. The display is configured to display the backup airspeed as the airspeed reference. The backup airspeed is generated based on Global Position System (GPS) information that is received by the aircraft.

Abstract: A system and method are provided for integrating and displaying the collective cue and the pitch and roll cue of a helicopter display with a flight path marker providing a moving reference showing the aircraft flight path.

Abstract: A method of determining a turbulent condition in an aircraft with a handheld device where the handheld device has at least one of a gyroscope, seismometer, and an accelerometer where the method includes receiving an output from the at least one of the gyroscope, seismometer, and accelerometer while the handheld device is located within the aircraft and providing an indication of a turbulent condition.

Abstract: A system and method for illuminating one or more sidestick controllers within a cockpit of an aircraft is described. In some embodiments, the system includes a sidestick controller having lighting components that display lighting behaviors representing the movement and/or control of an aircraft. In some embodiments, the system illuminates various different lighting components on a sidestick controller based on information received from aircraft control systems, cockpit lighting systems, and other systems associated with an aircraft.

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 and device for providing a pilot warning signal is provided, where such method can include providing a first signal to indicate a pedal angle of a pedal, providing a second signal which is directly dynamically dependent on the pedal angle, pairing up values of the first signal and the second signal at specific times, determining an angle change of the pairs of values and an increment of the pairs of values at two successive times, and generating the pilot warning signal when actuation of the pedal and a stimulated tumbling movement of the aircraft are ascertained and if the determined angle change of the pairs of values is greater than a first threshold value or the determined angle change of the increment of the pairs of values is greater than a second threshold value. A computer program product and a warning device are also provided.

Abstract: A method and apparatus for monitoring an aircraft. A pilot control input signal is received. A response of a control surface system controlled by a flight control model is identified using the pilot control input signal. An alert is generated when the control surface system reaches a threshold with respect to the control surface system becoming saturated.

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 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: 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: A method, apparatus, and computer program product for identifying air data for an aircraft. The lift for the aircraft is identified. The number of surface positions for the aircraft is identified. The angle of attack during flight of the aircraft is identified. A synthetic dynamic pressure is computed from the lift, the number of surface positions, and the angle of attack.

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: 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: An aviation yoke HSI interface and flight deck control indicator and selector safety system enhances flight safety. The system incorporates a multi-controlled HSI with a yoke heading adjustment control, a yoke radial/course selector, and a yoke heading centering control positioned on a yoke, stick, or collective. The system may also incorporate a first officer multi-controlled HSI with a first officer yoke heading adjustment control, a first officer yoke radial/course selector, and a first officer yoke heading and course centering control. An autopilot mode indicator visually indicates whether an autopilot is flying according to a desired heading or according to a navigational aid signal, such as a VOR radial signal. A side selector-indicator control permits selection of which side controls the flight of the aircraft.

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: Attitude and Configuration Indicator Display System and Method within the context of an Electronic Instrument System in which the configuration status of a piloted craft; typically the instant positions of lift inducing elements and drag inducing elements, are represented by symbol groupings integrated with an a parent icon, typically a chevron-type symbol representative of the piloted craft. The symbol groupings receive data from associated on-board sensors and are displayed singly or in combination with each other anytime the piloted craft is not in a clean configuration to instantly alert the pilot(s) of the configuration status with a single glance directed to the attitude indicator.

Abstract: The present invention relates to a tester, its use and a method for testing signal lines of a flight control system for a trimmable horizontal stabilizer (THS) motor of an aircraft. The tester comprises at least one test-relay (52, 54) to be connected with a relay socket of the flight control system, when the signal lines of the flight control system are to be tested, and at least one indicator (60, 70, 80, 90) being electrically connected with the at least one test-relay (52, 54) for indicating whether a voltage being applied to the test-relay (52, 54) is equal to or larger than a predetermined voltage. The method according to the invention comprises the steps of connecting at least one test-relay (52, 54) of a tester (1), in place of the original relay, with the relay socket of the flight control system, applying a voltage to the at least one test-relay (52, 54) and determining whether a voltage being applied to the at least one test-relay (52, 54) is equal to or larger than a predetermined voltage.

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: Attitude and Configuration Indicator Display System and Method within the context of an Electronic Instrument System in which the configuration status of a piloted craft; typically the instant positions of lift inducing elements and drag inducing elements, are represented by symbol groupings integrated with an a parent icon, typically a chevron-type symbol representative of the piloted craft. The symbol groupings receive data from associated on-board sensors and are displayed singly or in combination with each other anytime the piloted craft is not in a clean configuration to instantly alert the pilot(s) of the configuration status with a single glance directed to the attitude indicator.

Abstract: A spatial audio system for implementing a head-related transfer function (HRTF). A first stage implements a lateral HRTF that reproduces the median frequency response for a sound source located at a particular lateral distance from a listener, and second stage implements a vertical HRTF that reproduces the spectral changes when the vertical distance of a sound source changes relative to the listener. The system improves the vertical localization accuracy provided by an arbitrary measured HRTF by introducing an enhancement factor into the second processing stage. The enhancement factor increases the spectral differentiation between simulated sound sources located at different positions within the same “cone of confusion.

Abstract: Aircraft attitude systems are provided, in which a representative system includes: an instrument face having a bank angle scale, a bank status indicator, a pitch angle scale and a pitch status indicator; the bank angle scale being fixed in position relative to the instrument face and being operative to present increments of bank angle of an aircraft; the bank status indicator being operative to move relative to the bank angle scale such that a current aircraft bank angle is indicated; the pitch angle scale being fixed in a vertical orientation relative to the instrument face and being operative to present increments of pitch angle of an aircraft; the pitch status indicator being operative to move relative to the pitch angle scale such that a current aircraft pitch angle is indicated.

Abstract: The general field of the invention is, within the framework of the terrain anti-collision systems for aircraft, the presentation on the displays for aiding the piloting and the navigation of a simplified symbology suited to these critical situations. More precisely, the symbols comprise guidance indications in the depictions representing the horizontal and vertical situation indicators as well as speed instructions and altitude instructions, indications relating to the propulsion of the jets as well as guidance messages.

Abstract: A method of operating an aircraft comprising a cockpit with a flight deck having at least one flight display, a pilot's seat facing the flight deck, and a synthetic vision system producing a synthetic image for displaying on the at least one flight display.

Abstract: Present novel and non-trivial system, module, and method for generating non-linearly spaced graduations for a symbolic linear scale are disclosed. Symbology data representative of a scale having non-linear graduations is generated as a function of a graduation reference assigned to each graduation, navigation reference data provided from an appropriate source, and a constant. Navigation reference data comprises pitch attitude data and/or aircraft heading data, from which a symbolic pitch attitude scale and/or heading scale is generated. Current attitude and/or heading may be used as a central reference from which spacing is measured, and the value of the constant is dependent on the size of the scale occupied on the screen of a display unit. Each symbolic linear scale may be merged with data representative of the scene outside the aircraft and presented on the screen along with a flight path predictor mapped to the non-linear scale.

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: Methods and systems for operating an avionics system are provided. A set of data that is representative of traffic advisory information is received. A visual indicator is displayed to a user based on the set of data that is representative of the traffic advisory information. The traffic advisory information may be received by a user through a receiver and manually entered into an interface for viewing. Alternatively, the avionics system may automatically generate the visual indicator based on the traffic advisory information.

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: Disclosed is a method and device for detecting lateral dissymmetry of an aircraft. A control parameter determination unit is used to determine a current value of a control parameter representative of all roll control surfaces of the aircraft, and a control parameter comparison unit is used to compare the determined current value with a predetermined reference value. A current deflection angle of a lateral stick of the aircraft is also determined, and the determined current deflection angle is compared with a predetermined angle value. A visual alarm signal is output, when the current value of the roll control surfaces of the aircraft is greater than a predetermined reference value and the lateral stick is at a deflection angle that is greater than a predetermined angle value.

Abstract: A target information storage unit (203) stores information regarding a group of targets (target panels) which are disposed dispersedly on a virtual race course and which each have an objective speed set therefor. An operation input reception unit (201) receives an operation input for a moving object (racing car) to be run on the course. Then, a running condition managing unit (204) manages the running condition of the moving object based on this operation input. Meanwhile, a passage determination unit (206a) sequentially determines whether or not the moving object has passed on the course by contacting the respective targets, based on the managed running condition. Further, a speed comparison unit (206b) compares the speed of the moving object at the time of the passage and the objective speed of each target. Then, an evaluation unit (206) evaluates the operation input from a user based on the determination result and comparison result.

Abstract: Methods and systems for displaying a digital terrain to a user of a vehicle are provided. First, second, and third actual terrain data points are received. The third actual terrain data point is between the first and second actual terrain data points. If the third actual terrain data point is above a line interconnecting the first and second actual terrain data points, the first actual terrain data point is modified such that the third actual terrain data point is not above a line interconnecting said modified first actual terrain data point and the second actual terrain data point. A digital terrain is displayed to the user of the vehicle. The digital terrain includes a first digital terrain data point corresponding to the modified first actual terrain data point.

Abstract: Systems and methods for outputting instructions when a vehicle is not responding to a roll-angle alert. An example system includes one or more altitude sensors that determine one of altitude above ground level or barometric altitude, one or more roll-angle sensors that determine the roll-angle of the vehicle, and a processor. The processor receives the altitude and roll-angle information, determines if an excessive roll-angle condition exists based on the received altitude and roll-angle information, and generates a roll-angle alert signal if a roll-angle alert condition exists. The processor generates a roll-direction signal based upon vehicle position relative to the horizon and outputs the determined roll-direction signal via the one or more output devices, if one of the condition still exists after the time delay, the vehicle roll-angle has deteriorated away from the desired threshold, or the roll-angle rate is greater than a roll-angle rate threshold.

Abstract: Embodiments include systems and methods for assisting a pilot of an aircraft. The system includes a near-eye display and a processing subsystem. The near-eye display includes a transparent display panel that is adapted to be oriented in proximity to at least one eye of the pilot. The processing subsystem is adapted to receive aircraft data that indicates an attitude of the aircraft, and to determine whether the aircraft data indicates a potential spatial disorientation situation. When the aircraft data indicates the potential spatial disorientation situation, the processing system is adapted to cause the near-eye display to display an exterior display indicator overlying at least a portion of the windshield of the aircraft. The exterior display indicator includes a visual representation of an earth-based reference, and the exterior display indicator is oriented to indicate the attitude of the aircraft.

Abstract: The device includes a calculation unit to automatically calculate an overall thrust moment of the engines which represents a thrust asymmetry of the engines of a multi-engine aircraft, a determination unit to automatically determine, using this overall moment, a maximum roll rate, and a limiting unit to automatically limit a roll command using this maximum roll rate.

Abstract: A method and system for presenting environmental data including receiving environmental data from a sensor, processing the data to generate a graphical representation of the environment, wherein the view point of the graphical representation of the environment is a distance (d) and an angle (?) relative to a point in an aircraft, and presenting the graphical representation of the environment to a user on a display.

Abstract: Methods and systems for operating a display device are provided. A first image is caused to be displayed on the display device. The first image is at least representative of a field of view from on-board an aircraft. A second image is rendered over the first image on the display device. A luminance of at least a portion of the second image is temporally modulated.

Abstract: A system and method for generating lateral guidance image data and presenting information representative of the image data is disclosed. A system is disclosed for determining lateral guidance information based upon the elevation of terrain cells and a level of terrain threat associated with the elevation. A left or right turn angle, or both could be formed between a projected flight path and a vector extending to a tangent point of a terrain boundary to the left and right, respectively. The degree of angle could be determined for each, and lateral guidance image data based upon the boundary location of a level of terrain threat with respect to the projected flight path determined. A lateral processor provides an alert signal associated with the generation of the lateral guidance information and provide such signal to a crew visual and aural alerting system.