Abstract: A high-assurance headtracking system for a head worn display (HWD) incorporating ground-truth fiducials is disclosed. In embodiments, the headtracking system includes a camera fixed to a mobile platform (e.g., an aircraft cockpit) and oriented toward a pilot wearing the HWD. Images captured by the camera detect fiducial markers attached to the HWD (and fixed in a device reference frame) and static fiducial markers fixed to the mobile platform, each static fiducial marker including a constellation of individual markers having a known position and orientation in the platform reference frame. The headtracking system include control processors for analyzing the images and identifying therein the device-frame and static fiducial markers. The headtracking system determines a device pose of the HWD relative to the platform reference frame and monitors the device pose for drift or error based on the known positions of the identified static fiducial markers.

Abstract: A system is disclosed that display configured to transmit a signal that includes a first light configured as a display image and a second light configured as a reference image. The system also includes a beam splitter, a selectively transmissive mirror and a sensor configured to detect the second light. The beam splitter is configured to receive the signal from the display and reflect the signal to the selectively transmissive mirror. The selectively transmissive mirror is configured to receive the reflected signal, transmit the second light toward a sensor, and reflect the first light, wherein the first light is configured with a first bandwidth, wherein the second light is configured with a second bandwidth. The system further includes a corrector lens configured to receive the first light and transmit the first light to an exit pupil.

Abstract: A camera agnostic core monitor for an enhanced flight vision system (EFVS) is disclosed. In embodiments, a structured light projector (SLP) generates and projects a precise geometric pattern or other like artifact, which is reflected by collimating elements into the EFVS optical path. Within the optical path, the EFVS focal plane array is illuminated by, and detects, the projected artifacts within the scene imagery captured for display by the EFVS. Image processors assess the presentation of the detected artifacts (e.g., position/orientation relative to the expected presentation of the detected artifact within the scene imagery) to verify that the displayed EFVS imagery is not misleading.

Abstract: A camera agnostic core monitor for an enhanced flight vision system (EFVS) is disclosed. In embodiments, a structured light projector (SLP) generates and projects a precise geometric pattern or other like artifact, which is reflected by collimating elements into the EFVS optical path. Within the optical path, the EFVS focal plane array is illuminated by, and detects, the projected artifacts within the scene imagery captured for display by the EFVS. Image processors assess the presentation of the detected artifacts (e.g., position/orientation relative to the expected presentation of the detected artifact within the scene imagery) to verify that the displayed EFVS imagery is not misleading.

Abstract: A system is disclosed that display configured to transmit a signal that includes a first light configured as a display image and a second light configured as a reference image. The system also includes a beam splitter, a selectively transmissive mirror and a sensor configured to detect the second light. The beam splitter is configured to receive the signal from the display and reflect the signal to the selectively transmissive mirror. The selectively transmissive mirror is configured to receive the reflected signal, transmit the second light toward a sensor, and reflect the first light, wherein the first light is configured with a first bandwidth, wherein the second light is configured with a second bandwidth. The system further includes a corrector lens configured to receive the first light and transmit the first light to an exit pupil.

Abstract: A high-assurance headtracking system for a head worn display (HWD) incorporating ground-truth fiducials is disclosed. In embodiments, the headtracking system includes a camera fixed to a mobile platform (e.g., an aircraft cockpit) and oriented toward a pilot wearing the HWD. Images captured by the camera detect fiducial markers attached to the HWD (and fixed in a device reference frame) and static fiducial markers fixed to the mobile platform, each static fiducial marker including a constellation of individual markers having a known position and orientation in the platform reference frame. The headtracking system include control processors for analyzing the images and identifying therein the device-frame and static fiducial markers. The headtracking system determines a device pose of the HWD relative to the platform reference frame and monitors the device pose for drift or error based on the known positions of the identified static fiducial markers.

Abstract: A high-assurance headtracking system for a head worn display (HWD) incorporating ground-truth fiducials is disclosed. In embodiments, the headtracking system includes a camera fixed to a mobile platform (e.g., an aircraft cockpit) and oriented toward a pilot wearing the HWD. Images captured by the camera detect fiducial markers attached to the HWD (and fixed in a device reference frame) and static fiducial markers fixed to the mobile platform, each static fiducial marker including a constellation of individual markers having a known position and orientation in the platform reference frame. The headtracking system include control processors for analyzing the images and identifying therein the device-frame and static fiducial markers. The headtracking system determines a device pose of the HWD relative to the platform reference frame and monitors the device pose for drift or error based on the known positions of the identified static fiducial markers.

Abstract: A method of determining the angular orientation of headgear is described. The headgear has tracking points being at least four tracking points, the relative position of the tracking points is calibrated and stored as relative position information, each of the tracking points comprises an infra-red (IR) reflective point. Light reflected from at least some of the tracking points of the headgear is filtered to allow only light in an IR wavelength band to pass. The filtered IR light is imaged to provide a detected image including at least some of the tracking points. At least some of the tracking points in the detected image are identified, and the position of the identified tracking points in the detected image is determined. The angular orientation of the headgear is determined in multiple different angular directions based on the stored relative position information and the position of the identified tracking points.

Abstract: A method or system can be used with an aircraft or other vehicle. The system can include or the method can use a waveguide disposed above and below a top surface of a glare shield. The waveguide can be part of a head up display (HUD). The waveguide can be disposed to cover at least part of the head down display to provide an integrated display.

Abstract: Systems and a related method for monitoring commercial off the shelf (COTS) display devices in an avionics display system ensure that the COTS display devices are compliant with hazard classifications by positioning transparent photodetectors in the optical path to monitor the images and components generated and projected by the COTS display devices. Transparent photodetectors are positioned downstream in the optical path to monitor image orientation, refresh rate, or brightness of displayed images and image elements. The system may include transparent image sensors for capturing scene content and monitoring image integrity by comparing the captured scene content to the displayed images. Transparent image sensors positioned proximate to camera cores of an enhanced vision system (EVS) may verify the alignment of individual component image streams combined into an image stream displayed via HDD, HUD, HWD, or a like display element.

Abstract: A system and method for automatic boresighting of a head-tracking system for a HWD or HUD accesses georeferenced pose (position/orientation) data of an aircraft or other mobile platform from a georeferenced head-tracker and platform-referenced head pose data (based on fiducial markers within the aircraft cockpit) from the inertial measurement units of an optical, magnetic, or optical/magnetic platform-referenced head tracker (PRHT) and determines misalignments of the PRHT relative to the boresighted inertial reference system (IRS) of the aircraft. Based on the determined misalignments and accessed data, the IMUs of the PRHT may be updated and aligned with the aircraft boresight. Misalignments of head-mounted fiducial markers with the boresighted IRS may be determined for updating the alignment of an optical head-tracker fixed relative to the aircraft cockpit.

Abstract: A method or system can be used with an aircraft or other vehicle. The system can include or the method can use a waveguide disposed above and below a top surface of a glare shield. The waveguide can be part of a head up display (HUD). The waveguide can be disposed to cover at least part of the head down display to provide an integrated display.

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