Abstract: Avionics display system is provided for deployment onboard an aircraft and includes an air traffic data source that provides the avionics display system with data indicative of at least position and velocity of a neighboring aircraft. The system comprises a cockpit display system, and a monitor included within the cockpit display system. The cockpit display system receives and displays position and velocity data pertaining to the neighboring aircraft on the cockpit monitor as a position symbol and a velocity vector graphic. A processor operatively coupled to the monitor is configured to generate an air traffic display on the monitor including symbology indicative of (1) the current position of the neighboring aircraft (2) a velocity of the neighboring aircraft, and (3) the rate-of-change of the velocity of the neighboring 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: Apparatuses and methods for displaying autoflight information and controlling autoflight systems. In one embodiment, a flight deck for an aircraft having an autoflight system includes at least one pilot seat, at least one window positioned forward of the pilot seat, and a forward instrument panel positioned forward of the pilot seat. In one aspect of this embodiment, the forward window provides a forward field of view out of the aircraft for a pilot seated in the pilot seat. In another aspect of this embodiment, the flight deck further includes a display device configured to provide information related to one or more autoflight modes. The display device can be positioned at least approximately between the forward instrument panel and the forward window to provide the pilot with autoflight information at least proximate to the forward field of view. In a further aspect of this embodiment, the display device can be configured to provide information related to one or more target flight parameters.

Abstract: A near-to-eye display allows an operator of a vehicle, such as a pilot of an aircraft, to see an obstacle on a conformal pathway, such as a runway or taxiway. The obstacle may be boundaries of the pathway or an object captured by an optional Infrared camera.

Abstract: Methods for flying multiple aircraft in a predetermined formation in which a relative navigation grid is emitted from at least one of the aircraft, a spatial relationship is calculated based on the emitted relative navigation grid, and a relative position of at least one aircraft is altered to position the aircraft in the predetermined formation when the spatial relationship does not conform with the predetermined formation.

Abstract: An image display apparatus includes: an image generation unit generating a plurality of images with different figure sizes so that perceived positions of the plurality of images are sequentially located in a direction away from an actual position; a reflection member provided in front of the observer; and a projector projecting a light beam to form, the plurality of images onto a single eye of the observer through the reflection member so that the plurality of images is superimposed on a background observed through the refection member.

Abstract: A display system comprises first and second LED panels for displaying first and second priority aviation data, a power supply, a modulator, a processor and a logic gate. The modulator generates a modulated voltage for the second LED panel, where the second priority data are displayed at a modulated brightness. The processor controls the modulator, and generates a status signal indicating a failure condition of the modulated voltage. The logic gate switches the first LED panel from the modulated voltage to the unmodulated voltage based on the status signal, where the first priority data default from the modulated brightness level to full brightness based on the failure condition.

Abstract: A vehicle windshield display system for detecting obstruction of a vehicle operator's field of view by a windshield display. The system provides closed-loop feedback to perform a visual check of what is actually being displayed on a windshield display in order to avoid obstructing an operator's field of view. The system includes a windshield display configured to be installed into a vehicle and configured to display a graphic in a field of view of an operator of the vehicle, a camera configured to determine an image of the graphic displayed by the windshield display, and a controller configured to determine if the image indicates that field of view is obstructed. The camera is used to monitor the windshield display and provide feedback to the controller so that appropriate adjustments to the graphic being displayed can be made.

Abstract: A method for displaying a visual warning signal to warn a driver of a vehicle about a traffic situation that is determined to be critical. The visual warning signal displayed to the driver is based on sensor data furnished by at least one sensor unit that determines a line of sight of the driver. A display unit for displaying the visual warning signal is selected from a group of at least two separately controllable display units depending on the line of sight of the driver.

Abstract: A low visibility landing system is provided for guiding aircraft on landing approaches. The low visibility landing system may aid a pilot during landing in low visibility conditions such that an aircraft may descend to lower altitudes without visual contact with the runway than is possible with other landing systems. The system may use various navigational systems to produce a hybrid signal that may be more stable than individual signals of those navigational systems. The hybrid signal is compared to a predetermined landing approach plan to determine the deviation of the aircraft from the landing approach plan and to provide guidance to the pilot to get the aircraft back onto the landing approach plan. The system may also use multiple navigational systems to perform checks on an operation of a primary navigational system to ensure that the primary navigational system is operating accurately.

Abstract: Systems and methods for efficiently updating text or symbol annunciations outputted by an avionics system on legacy displays. Instead of using a set sweeping pattern to update the display, a smart updating concept is used. The smart updating concept senses when the pilot is adjusting the selected altitude control (or other user interface device that will alter displayed annunciations), then gives priority to updating the radial lines on the display that contain the annunciation field. Once the annunciation field has been updated, the display returns to normal operation.

Abstract: Methods and apparatus are provided for selecting a touchdown point for a vertical takeoff and landing aircraft. The eye movements of a user are tracked relative to an image being rendered on a display screen. An updated touchdown point location is determined from the tracked eye movements, and an updated touchdown point is rendered at the updated touchdown point location on the display screen.

Abstract: A method and apparatus for searching and generating trajectory content in a navigation device are provided. The method includes establishing a predetermined search region from a current position; extracting information about first parcels included in the established search region and information about second parcels including information about links of specific trajectory content; and determining whether the specific trajectory content is included in the established search region by comparing the information about the first parcels with the information about the second parcels.

Abstract: An aircraft system includes a visual display system; a printer; and a flight management system coupled to the visual display system and the printer. The flight management system includes a processor and a plurality of data sources coupled to the processor. The processor includes a crew interface module coupled to the plurality of data sources, a display driver coupled to the crew interface module and the visual display system, and a printer driver coupled to the crew interface module and the printer. The crew interface module is configured to generate a report from data from the data sources and to send the report to the visual display system via the display driver. The visual display system is configured to receive the report and to display the report.

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

Abstract: An image display apparatus includes: a left-eye light source (101) that outputs a left-eye image constituting an original image in whole or in part; a left-eye deflection unit (104) that deflects, toward a left eye of the user, the left-eye image outputted by the left-eye light source (101); a right-eye light source (110) that outputs a right-eye image constituting the original image in whole or in part; a right-eye deflection unit (107) that deflects, toward a right eye of the user, the right-eye image outputted by the right-eye light source (110); and a control unit (105, 111) that controls the left-eye light source (101) and the right-eye light source (110) such that the left-eye image and the right-eye image are outputted which are different from each other in at least one of pixel position, image shape, image size, image resolution, and display frame rate so that the user can recognize the original image from the left-eye image and the right-eye image by an image fusion effect.

Abstract: Systems and methods are provided for displaying information on a display device associated with an aircraft. A method comprises rendering a perspective view of terrain on a display device and obtaining sensor data for a sensing region overlapping at least a portion of the viewing region. The method further comprises obtaining tracking data associated with a first object located within the sensing region and correlating a first portion of the sensor data that corresponds to the first object with the tracking data. The method further comprises rendering a graphical representation of the first object on the display device, wherein positioning of the graphical representation of the first object with respect to the terrain is influenced by the correlation with first portion of the sensor data.

Abstract: A present novel and non-trivial system, apparatus, and method for presenting a monochrome, three-dimensional image of terrain on a Head-Up Display (“HUD”) unit is disclosed. Based upon aircraft navigation and terrain data, an image data set representative of a lighted solid image of terrain comprised of a plurality of intensities of one color may be generated. The image data set may be determined as a function of terrain data and color intensity data, where the color intensity data could be comprised of one or more shading effects, one or more texturing effects, or a combination of both. Based upon the image data set, a three-dimensional perspective of a terrain scene outside the aircraft may be presented to the pilot.

Abstract: A present novel and non-trivial system, module, and method for varying the intensity of a visual aid depicted on an aircraft display unit. Visual aids could represent visible features such as markings on a runway surface. Data representative of visual aids may be provided by a navigation reference data source with errors inherent in the data which may be measured by one or more quality parameters. Also, errors associated with quality parameters are inherent in navigation data which provided positional information. Because of these errors, the depiction of visual aids on an egocentric display unit may appear misaligned with the corresponding visible feature. To compensate for the misalignment, an image generating processor generates visual aid data representative of at least one variable-intensity visual aid, wherein the intensity of each visual aid varies and such variation is based upon at least one quality parameter of the data.

Abstract: A method and device to assist in the piloting of an aircraft in a landing phase may apply a maximum braking of the aircraft if there is a risk of longitudinal departure from a runway.

Abstract: A present novel and non-trivial system, module, and method for presenting runway advisory information are disclosed. A runway reference may be established using data received from a source of navigation reference data, where such data could represent runway information, runway awareness zone information, landing awareness zone information, and/or runway threshold line information. Navigation data representative of at least aircraft location and input factor data may be received from a source. Phase of flight may be determined using input factor data, and a runway advisory data set may be generated as a function of phase of flight and the positional relationship between aircraft location and the runway reference. Runway advisory data set may be representative of advisory information comprised of visual runway advisory information, aural runway advisory information, tactile advisory information, or a combination thereof.

Abstract: Context-Sensitive Reference (CSR) for situational awareness, and associated methods and systems are disclosed. A system in accordance to one embodiment includes an aircraft display system having a traffic application with traffic symbols representing traffic aircraft and a CSR associated with traffic aircraft displayed proximate to the respective traffic symbol. The CSR improves situational awareness of the traffic scenario by further refining the depiction of actual traffic on a traffic display relative to own-ship suitable to the traffic situational awareness need at hand. Such depiction may be in time or distance relative to own-ship or to fixed structure, and engaged in an automatic or manual mode.

Abstract: A display system for displaying information to a vehicle operator comprises one or more projectors positioned in an operator cab of a vehicle. The projector is configured to project a heads up display of a plurality of data sets on a windscreen of the vehicle. Projected data sets are positioned in the heads up display and/or moved within the heads up display based on assessed relative priority levels of the data sets. Thus, for example, a data set with a higher assessed relative priority level may be positioned in a location of greater operator viewing prominence. If the priority level drops, the data set may be moved to a position of lower operator prominence. Respective heads up displays may be projected on more than two separate windscreens of the vehicle, either simultaneously or at alternate times, and possibly depending on an operational mode of the vehicle.

Abstract: The invention provides, in some aspects, aviation navigational systems and methods for cockpit display of traffic information that generate intuitive three-dimensional graphical representations of air traffic (and/or other potential conflicts) in the vicinity of an aircraft in flight, as well as during take-off and landing. These systems and methods provide improved awareness of potential conflicts, offering in the cockpit an immediate understanding of the significance of potential conflicts, e.g., vis-à-vis their nature, direction, and time to visual contact. Thus, according to one aspect of the invention, there is provided an aviation navigational system that generates a 3D representation of the airspace in the vicinity of an aircraft and, relative to that representation, a representation of air traffic in that airspace.

Abstract: The present disclosure is directed to a dynamic field of view (FOV) for a synthetic vision system (SVS) scene. The FOV within the SVS scene may switch between a FOV conformal to the real world outside of a vehicle and a wider FOV when beneficial. In an aircraft, for example, generating the SVS scene with the narrower FOV may be optimal during flight, while on the ground a wider FOV may improve situational awareness during taxiing. Determination of the airborne or grounded status of the aircraft may be based on speed, altitude, user input, or a received signal. Although the foregoing has been described within a particular context, the present disclosure is not limited to this scenario and may be applied to any vehicle in any situation where dynamically changing between a narrower FOV and a wider FOV is beneficial.

Abstract: The invention is directed to a display device for working vehicle, which is adapted so that additional information can be displayed. In the invention, display indication marks of the two types can be interchangeably displayed on a common display screen of a limited area without reducing the sizes of the individual marks, so that neither a larger size of a display device nor a drop in the visibility of the indication marks is necessary. This enables the driver to control a working machine such as a construction machine and have additional information about the construction machine without any trouble in the driving.

Abstract: The invention pertains to optoelectronic devices for aiding the guidance and taxiing of aircraft, comprising a so-called head-up collimator allowing the presentation of information in the pilot's visual field. It applies notably to large-size civil aircraft of the Boeing 747 or Airbus A380 type. The optoelectronic device comprises means for calculating a deviation factor for the actual trajectory of said aircraft relative to a theoretical trajectory on said traffic way, means for generating symbols and at least one head-up collimator comprising means for displaying and superimposing said symbols on the outside landscape. The deviation factor is calculated on the basis of an angle (PÂ?G) and that the means for generating symbols generate a symbol representing said deviation factor, so as to be superimposed on said traffic way.

Abstract: A see-through display system includes a processing unit configured to receive data representative of geo-referenced symbology and terrain data, to compare the geo-referenced symbology to the terrain data, and to generate display commands associated with the geo-referenced symbology based on the terrain data. The system further includes a display device coupled to the processing unit and configured to receive the display commands from the processing unit and to display the geo-referenced symbology.

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: A terrain advisory display including a display, a processing circuit coupled to the display and wherein the display is configured to generate a three-dimensional image.

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: There is provided a vehicle having a simple and inexpensive structure that assists the driving sense. A front window shield 1 of a vehicle 100 is provided with a pair of marks 2 and 3 substantially horizontally aligned. The marks 2 and 3 are formed at the same height at the left and right sides of the front window shield 1. A driver perceives a virtual line L by the marks 2 and 3 on the front window shield 1, and trackings the line of sight W1 are induced to move such as to gather between the bottom end line (herein, a line of an instrument panel 6) and a virtual line L.

Abstract: A display device, having a traffic lane recording, in which lane markings of the recorded traffic lane are shown in the display in such a way that the quality of the traffic lane recording can be discerned.

Abstract: The general field of the invention is that of systems for aiding the guidance of an aircraft on an airport. The system according to the invention comprises means for determining at least one element of the topology of the airport in relation to the position of the aircraft for selecting. Selecting means are provided by the pilot of the aircraft for the element. Generating means are provided to generate at least one guidance or safety set-point using the topological element. Presenting means are provided for the element or the associated set-point on a man-machine interface to the pilot of the aircraft.

Abstract: A system for providing taxi navigation information to a pilot of an aircraft is comprised of a navigation system; a taxi navigation module consisting of, in part, a processor and database; and an indicating system consisting of, in part, a tactical display unit system (e.g., a primary flight director (“PFD”), and head-up display (“HUD”) of an aircraft. A navigation system may provide aircraft position data of the aircraft while it is on the ground. A processor receives the aircraft position data, retrieves taxi navigation symbology based upon the aircraft position data from a taxi navigation database, and provides this data to the indicating system. The indicating system generates the display of taxi navigation information on a display unit which, in turn, provides the pilot with an egocentric view of airport signage using colored aviation signage symbology.

Abstract: The embodiments disclosed herein present novel and non-trivial system, module, and method for creating a variable FOV image presented on a HUD combiner unit. A processor receives navigation system data and data associated with eye position. A variable FOV image data set representative of navigation symbology is generated, where the image data set is determined by applying the navigation system and eye position data to an adaptive FOV function, where the function correlates eye position to an FOV image. The image data set is presented to a HUD system where an image represented in the image data set is displayed on a combiner unit, whereby the image FOV correlates to eye position. Furthermore, the processor may receive terrain data and generate a variable FOV image data set inclusive of data representative of a three-dimensional perspective scene outside an aircraft.

Abstract: A display system is provided that renders a horizontal situation indicator that includes required navigation performance (RNP) and estimated position uncertainty (EPU) values rendered non-numerically and in a fairly intuitive manner. A processor receives at least data representative of a desired course of the aircraft, data representative of the RNP for the aircraft, and data representative of the EPU for the aircraft. The processor renders, on a display device, a horizontal situation indicator that includes an aircraft symbol representative of a top-down view of the aircraft, an RNP boundary graphic representative of at least one RNP boundary for the aircraft, and an EPU graphic representative of the EPU for the aircraft. The aircraft symbol is rendered at a position that is representative of actual aircraft position relative to the desired course, and the RNP boundary graphic is rendered at a position relative to the rendered aircraft symbol.

Abstract: A display system for vehicle includes an outside information-obtaining section configured to obtain outside information of a moving object; a position-detecting section configured to detect a position of one eye of an image viewer getting on the moving object; and an image-projecting section. The image-projecting section is configured to obtain a position of a target in the outside information obtained by the outside information-obtaining section, to generate a display object on the basis of the obtained position of the target, and to project a light flux including an image having the generated display object toward the one eye of the image viewer on the basis of the detected position of the one eye.

Abstract: An aircraft display system is provided that is configured to render a perspective display having a field of view. The aircraft display system includes a monitor and a processor coupled to the monitor. The processor is configured to generate a map display on the monitor. The map display indicates the value of at least one parameter of the field of view of the perspective display.

Abstract: An aircraft communications system is located on an aircraft. The aircraft communications system comprises a set of eyewear units, an aircraft data processing system, and a wireless system. Each eyewear unit has a set of sensors and a display. The set of eyewear units is capable of receiving user input and is capable of presenting information to a set of users of the set of eyewear units. The aircraft data processing system is capable of receiving the user input and sending the information to the set of eyewear units in response to receiving the user input from the set of eyewear units. The wireless system is located proximate to the cabin of the aircraft and is capable of sending the user input from the set of eyewear units to the aircraft data processing system and sending the information to the set of eyewear units.

Abstract: A head-up display (HUD) is disclosed. The HUD is on board a rotary wing aircraft. The HUD comprises a projector. The HUD also comprises a combiner. The combiner enables viewing of the world outside of the combiner and allows viewing of information provided from the projector. Further, the HUD comprises a computer coupled to the projector in providing hover and touchdown symbols conformally mapped onto the combiner. A conformal mapping of hover and touchdown symbols is also provided on the combiner.

Abstract: A synthetic vision system (SVS) for an aircraft, including a user input device for receiving runway correction commands from a user. The runway correction commands are in response to discrepancies observed by the user between an observed runway position in the real world and a synthetic vision runway position depicted on an electronic display device. The user input device provides runway corrections. An SVS computer is operatively connected to the electronic display device for providing SVS image data to the electronic display device in response to received runway parameter data. A runway parameter server device (RPSD) is operatively connected to the user input device and to the SVS computer for receiving the runway corrections from the user input device and providing the runway parameter data, including any corrected data provided by the user, to the SVS computer.

Abstract: A method is provided for indicating the boundaries of a required navigational performance (RNP) corridor on an aircraft's map display. The method includes the steps of producing an aircraft leg segment symbol on the map display, establishing an RNP value, and scaling the RNP value to the map display field of view. The method further includes the step of generating an RNP corridor boundary graphic on the map display offset from the aircraft leg segment symbol by the scaled RNP value.

Abstract: The invention relates to a system with a device for determining the current position of the aircraft, a display device displaying, on a viewing screen an airport map, wherewith is associated a symbol illustrating the current position of the aircraft, an interface device enabling the display of the display device to be operated by an operator, a storage device storing a plurality of airport maps, a device for determining a reference point for each airport, whereof the map is stored in the storage device, and a selecting device which selects an airport map stored in the storage device so as to transmit same to the display device so that it can be displayed, and which comprises a device enabling an airport map to be automatically selected, based on the current position of the aircraft and as airport reference point.

Abstract: A display system for an aircraft includes an automatic reconfiguration device that, upon detecting a failure of a screen of the system, displays an image that is associated with the failed screen on an associated valid screen having lesser priority.

Abstract: A display system for an aircraft includes a device for controlling the presentation on a head-down screen of primary piloting information during a detected display defect on a head-up display device, which normally displays such primary piloting information.

Abstract: A system and method for displaying aircraft glide slope includes determining a glide slope deviation that is representative of a difference between a desired aircraft glide slope and an actual aircraft glide slope. A glide slope icon that is representative of the desired aircraft glide slope and a glide slope deviation icon that is representative of the determined glide slope deviation are simultaneously rendered on a display.

Abstract: A display device for a vehicle is provided, by which a driver of the vehicle is free from a trouble of adjusting a display position of the virtual image without cost-up of the device. When the support start detecting means detects a support start timing of adjusting a reflection angle, for example, a timing of an operation of an operation switch or a start of an operation, the rotation control means controls the rotating means so that the reflecting member having a reflection angle indicated by the reflection angle data stored in the reflection angle data storing means is (a) rotated within an adjustment supporting range on a condition that the reflecting member is reflecting the display light from the display source and (b) returned to a reflection angle indicated by the reflection angle data.

Abstract: An aircraft standby display device includes a set of data sources, a data processing unit, and a display. The display presents altitude control indicators representing speed, altitude, attitude, and a heading scale that includes a characteristic symbol indicating a next route point of an aircraft flight plan. The heading scale is independent of the altitude control indicators. The display also presents a quantitative value that: (1) indicates the remaining distance of flight of the aircraft to reach the next route point and (2) is associated with the characteristic symbol.

Abstract: A system for multi-modal cockpit interface during surface operation of an aircraft comprises a head tracking device, a processing element, and a full-color head worn display. The processing element is configured to receive head position information from the head tracking device, to receive current location information of the aircraft, and to render a virtual airport scene corresponding to the head position information and the current aircraft location. The full-color head worn display is configured to receive the virtual airport scene from the processing element and to display the virtual airport scene. The current location information may be received from one of a global positioning system or an inertial navigation system.