Abstract: An apparatus provides a virtual display in an environment for various applications including avionic, naval, military, remote control, medical and other applications. The apparatus can be a near eye display, such as, a head up display (HUD) or head worn display (e.g., helmet mounted display (HMD), glasses-based, goggle-based, visor-based, etc.). The near eye display can include a combiner for providing one or more of: an image for a failed display, an image between two or more head down displays, or an image to direct attention to warnings or locations in the field-of-view of the combiner.

Abstract: A system for enhancing an image displayed on a display unit of an aircraft is shown and described. The system includes an enhanced vision system that detects a scene and enhances the scene for display on the display unit. The enhanced vision system includes a sensor having a filter configured to filter out all but at least one narrowband spectrum of light from the scene to detect elements of a first color. The enhanced vision system causes remaining content of the scene to be removed from the filter output for completing the detection of the elements of the first color. The enhanced vision system enhances the elements of the first color on the display unit.

Abstract: Provided in one embodiment is a method of detecting a pulsing signal, comprising: detecting the pulsing signal using a first sensor device acquiring data at a first time interval; and detecting the pulsing signal using a second sensor device acquiring data at a second time interval; wherein the second time interval overlaps a portion of the first time interval.

Abstract: Present novel and non-trivial system, device, and method for combining image data received from two or more vision systems are disclosed. A system may be comprised of a first vision source, a second vision source, and an image generator (“IG”). The first vision source may be could configured to generate a first image data set and a depth buffer data set, and the second vision data source could configured to generate a second image data set. The IG could be configured to receive both the first and second image data sets; the depth buffer data set; and generate a third image data set as a function of both image data sets, the depth buffer data set, and a pixel cutoff distance that may be fixed or variable. In addition, the pixel cutoff distance may be determined as a function of input variable data.

Abstract: Present novel and non-trivial system, device, and method for preventing artifacts in an electromagnetic imaging system are disclosed. A processing unit may be configured to receive or derive exposure data corresponding to an exposure of electromagnetic radiation; identify each cell of the exposure data exceeding a maximum exposure limit; generate address data representative of an address of each identified cell; and send the address data to a modifiable medium such as (1) an array of reflecting devices that are modifiable through repositioning techniques, (2) an array of transmissive devices that are modifiable to prevent the passage of radiation, and/or (3) an occulting disk whose position is modifiable to prevent the passage of radiation. The exposure data could be comprised of actual exposure data received from a radiation detector. Alternatively, the exposure data could be comprised of calculated exposure data.

Abstract: A system for controlling an image displayed on a display unit of an aircraft is shown and described. The system includes an enhanced vision system that detects elements of an approach lighting system for display on the display unit. The system also includes a synthetic vision system that uses a database of navigation information and a determined aircraft location to generate synthetic display elements representing the approach lighting system. Display electronics of the system cause the detected elements from the enhanced vision system to be simultaneously displayed on the display unit within a same scene as the generated synthetic display elements from the synthetic vision system. Advantageously, the simultaneous display allows a pilot viewing the display unit to check for whether information provided by the enhanced vision system matches information provided by the synthetic vision system.

Abstract: A present novel and non-trivial system, device, and method for generating object symbology are disclosed. A system may be comprised one or more aircraft systems and a cockpit display system comprised of a system configuration file, a plurality of definition files, and a windows generator (“WG”). The WG may be configured to perform initialization and run-time operations. The initialization operation may be comprised of retrieving a system configuration file; retrieving a first definition file comprised of a first layer; and retrieving one or more second definition files comprised of one or more second layers. The run-time operation may be comprised of receiving a first-layer widget data set; receiving one or more second-layer widget data sets; determining each screen array cell; and generating a pixel data set in response to the determination.

Abstract: A method for monitoring inactive pixels in a scene imaging system may include determining a location of at least one inactive pixel in a focal plane array. The method may include sensing an environment image based upon a surrounding environment of an aircraft. The method may include generating an image associated with the environment image. The method may include evaluating a location for one or more inactive pixels in the generated image in comparison to a location for the at least one inactive pixel in the focal plane array. The method may include determining whether a fault exists in image generation or image display based upon the evaluation.

Abstract: An enhanced vision system for an aircraft is disclosed. The invention includes a display apparatus having a display element positioned between the pilot and a scene. The display element permits the pilot to view the scene therethrough. A first sensor is mounted adjacent to the display element. The first sensor is configured to detect light having a first radiation spectrum emanating from a first portion of the scene. A second sensor is mounted upon the aircraft away from the display element. The second sensor is configured to detect light having a second radiation spectrum emanating from a second portion of the scene. The display element is configured to visually represent the detected light with the first radiation spectrum precisely conformal with the scene as viewed by the pilot. The display element is configured to visually represent the detected light with the second radiation spectrum substantially conformal with the scene as viewed by the pilot.

Abstract: A method of increasing positional awareness of a pilot of an aircraft during a landing approach of the aircraft. First data from a navigational aid is received. The first data is analyzed to determine a first position of the aircraft at a predetermined time. Second data is received. The second data is independent of the first data. The second data is analyzed to determine a second position of the aircraft at the predetermined time. The first position of the aircraft and the second position of the aircraft are compared, and the pilot is alerted to a difference between the first position of the aircraft and the second position of the aircraft. The second data may be displayed in a form that is convenient for the pilot to view during landing.