Abstract: A synthetic visual system for an aircraft may comprise: a camera in electronic communication with a controller; a radar system in electronic communication with the controller; a three-dimensional cockpit display in electronic communication with the controller via a synthetic weather system; and a tangible, non-transitory memory configured to communicate with the controller. The three-dimensional cockpit display may be configured to display a three-dimensional weather image based on correlated data between the radar system and the camera.

Abstract: An aircraft hazard warning system or method can be utilized to determine a location of turbulence, hail or other hazard for an aircraft. The aircraft hazard warning system can utilize processing electronics coupled to an antenna. The processing electronics can determine an inferred presence of a weather condition in response to lightning sensor data, radar reflectivity data, turbulence data, geographic location data, vertical structure analysis data, and/or temperature data. The system can include a display for showing the weather condition and its location.

Abstract: A receiver system for correlating one or more signals (beam patterns) is disclosed. One or more antenna elements are configured to receive the signals. A controller generates correlator outputs based on a first set of duplicated signals, generates a first set of beams based on the one or more correlator outputs using a first beamforming module, generates a second set of beams based on a second set of duplicated signals using a second beamforming module, generates one or more power estimates based on the second set of beams, and divides each of the first set of beams by a corresponding power estimate to generate one or more normalized correlations.

Abstract: A parachute retention system may include a container and a replaceable flap. The container can be attached to a vehicle and can hold a parachute. The container may have a first attachment member. A replaceable flap may have a second attachment member that connects to the first attachment member and that has a flexible barrier portion for enclosing at least a portion of the container to retain the parachute therein.

Abstract: A parachute assembly may comprise a canopy and one or more reefing lines. The one or more reefing lines may limit inflation of the canopy to attenuate impulse load or otherwise mitigate forces exerted by the parachute assembly on cargo or an occupant during deployment of the canopy. The one or more reefing lines may be broken in stages to selectively limit inflation of the canopy followed by selectively permitting inflation of the canopy in stages.

Abstract: A roll stabilization system for an aircraft ejection seat may be provided. An integral seat sequencer may activate an ejection sequence causing an aircraft ejection seat to be ejected from an aircraft. In various instances, particularly with lighter occupants of the aircraft ejection seat, the aircraft ejection seat may begin a rotational movement. To ameliorate this rotational movement, a roll correction rocket motor is installed on the aircraft ejection seat and selectively activated by the integral seat sequencer in the event that an undesired rotational movement is detected.

Abstract: A system for detecting an alignment of a relay lens assembly and a combiner of a head-up display is disclosed. The system includes an illuminated reticle spatially coupled to the relay lens assembly, an optical sensor spatially coupled to the combiner, and a control module configured to receive an input from the optical sensor, determine a position of the combiner relative to the relay lens assembly based on the received input; and generate an output based on a determined position of the combiner relative to the relay lens assembly. In another system, the illuminated reticle is spatially coupled to the combiner, and the optical sensor is spatially coupled to the relay lens assembly. The system may also participate in a feedback loop with the head-up display to reduce jitter in the head-up display.

Abstract: A cabin control apparatus for installation in a cabin surface of an aircraft or other vehicle includes a set of haptic display devices in a housing, each haptic display device having a compact touch-sensitive display surface via which a passenger or user may provide control input for cabin services (e.g., lighting, seat adjustment, crew call, in-flight entertainment (IFE)). Each haptic display device includes haptic actuators for simulating the movement and feel of a mechanical button or switch. Each haptic display device provides information to the user as to the currently controlled cabin service or system, and the set of devices may be toggled between different operating modes wherein the set of devices controls a different set of services. Cabin services and systems controlled by the cabin control module may include passenger-specific context as well as network context, e.g., based on the time of day or the position of the vehicle.

Abstract: A method for updating a cryptographic key via a computation unit configured with one or more processors and a memory coupled to the one or more processors is disclosed. The method includes loading a base key into a cryptographic storage unit integrated with a cryptographic application. The method includes generating a temporal key based on the base key using a one-way key update algorithm via cryptographic application logic integrated within the cryptographic application. The temporal key is assigned an update count based on the number of updates performed on the temporal key. The method further includes comparing the update count value to a required update count, updating the temporal key if the update count is less than the required update count, and zeroizing the temporal key if the update count is more than the required update count, in which the temporal key may be regenerated with the required update count.

Abstract: A self-deploying counter for an aircraft monument is disclosed. In embodiments, the monument is installable adjacent to a cabin space within an aircraft passenger cabin (e.g., on either side of an exit door) and the self-deploying counter includes a partition door capable of being pivoted between a default closed position and an open position extending into the cabin space. The self-deploying counter has a horizontal top surface and an undersurface. When the partition door is deployed, the counter pivots in concert with the door's deployment, the fully deployed position corresponding to the open position of the partition door.

Abstract: A cold plate apparatus is disclosed. A cold plate includes a first set of sinusoidal conduits and a second set of sinusoidal conduits formed therein. The first set of sinusoidal conduits is arranged in a first direction, and the second set of sinusoidal conduits is arranged in a second direction. Crests of the first set of sinusoidal conduits overlap troughs of the second set of sinusoidal conduits. Crests of the second set of sinusoidal conduits overlap troughs of the first set of sinusoidal conduits. A first set of header plates is fluidically coupled to the first set of sinusoidal conduits, and a second set of header plates is fluidically coupled to the second set of sinusoidal conduits.

Abstract: An endurance haptic system is disclosed herein. The endurance haptic system includes a plurality of tactors, a plurality of air bladders, a tactor driver operably coupled to the plurality of tactors and configured to send vibration commands to the plurality of tactors in response to a first signal received from an aircraft controller, and an air bladder driver operably coupled to the plurality of air bladders and configured to inflate and deflate the plurality of air bladders in response to a second signal received from the aircraft controller.

Abstract: A system is disclosed herein, including a cushion including a plurality of tactors and a plurality of air bladders disposed adjacent the plurality of tactors, a pump assembly operably connected to the plurality of bladders, a processor, and a memory operatively coupled to the processor. The memory includes instructions stored thereon that, when executed by the processor, cause the processor to determine an inflation sequence for the plurality of air bladders, determine a deflation sequence for the plurality of air bladders, output commands to the pump assembly corresponding to the inflation sequence and the deflation sequence, and output vibrate commands to the plurality of tactors.

Abstract: A system may include a computer readable medium and a processor communicatively coupled to the computer readable medium. The processor may be configured to: obtain a graphical image file, the graphical image file including an image, wherein the image includes at least one sequence of repeating pattern elements, each of the at least one sequence including the repeating pattern elements that are repeated along a linear direction; and convert the graphical image file to at least one file including hardware directives that when executed cause a recreation of the image of the graphical image file to be drawn, wherein a file size of the at least one file is smaller than the graphical image file.

Abstract: A system and method for conformal alignment of an aircraft-based head worn display (HWD) system defines far-field features in view of the HWD display, each far-field feature having a 3D truth position in a navigational reference frame. The aircraft GPS/IRS determines pointing vectors to each feature in the aircraft reference frame. The HWD user estimates a nominal head pose for orienting the far-field features in the HWD display, and the HWD system renders the far-field features based on the nominal head pose and pointing vectors. The rendered far-field features are aligned to their real-world 3D truth positions (either manually or with the assistance of witness cameras) and a latched pose of the HWD headtracker system determined based on a successful alignment within accuracy bounds. Based on the latched headtracker pose, the HWD headtracker alignment and the alignment of the HWD display reference frame to the aircraft reference frame are updated.

Abstract: A communications system for line-of-sight (LOS) and beyond-line-of-sight (BLOS) communications using a single aperture includes one or more operators positioned within an environment, wherein each operator includes a common aperture, one or more low-earth orbit satellites communicatively coupled to a plurality of communications sub-systems disposed on the operators. In one embodiment, the communications sub-systems may include a first antenna element to transmit and receive first radio frequency signals along a first directional link via the common aperture. In another embodiment, the communications sub-systems may include a second antenna element to transmit and receive second radio frequency signals along a second directional link via the common aperture.

Abstract: A system and method for displaying dynamic time-based ranging over a moving map determines position, heading, and airspeed information of an ownship. Based on the positioning information of the ownship, the moving map projects the ownship forward in time and superimposes on the moving map (which may already include distance-based ranging information) time-based ranging information indicating a projected range of positions of the ownship at future or subsequent times relative to the current time. The displayed time-based ranging indicators may be arcuate in shape but adjusted to account for dynamic factors such as headwinds or tailwinds that may affect the time required for the ownship to reach a target at a given distance.

Abstract: A helmet assembly for a spacesuit or other protective suit is disclosed. In embodiments, the helmet assembly includes an external face shield attachable to the spacesuit and providing the spacesuit user with a forward field of view. The helmet assembly includes suit status displays hard-mounted to the external face shield at a periphery or edge of the forward field of view (e.g., upper, lower, left, right). Each suit status display includes a linear or one-dimensional array of individual light emitting diodes (LED) in communication with a suit controller of the spacesuit. Each LED array receives from the suit controller suit status data (e.g., consumables levels, suit performance, position data) communicated to the user by illuminating one or more of the individual LED units.

Abstract: A system and related methods for providing unusual attitude symbology for recovering from an unusual attitude condition. By the unusual attitude symbology, a pilot may visually determine corrective actions needed to recover from the unusual attitude condition with a minimal recovery time and similarly with a minimal cognitive workload. The pilot may thus establish stable flight, even under a high-stress situation. The unusual attitude symbology includes pitch direction indicators, roll direction indicators, a roll recovery arc, an unusual attitude warning indicator, and a roll entry chevron. Path based symbology may also be used to provide unusual attitude recovery while maintaining spatial orientation of the aircraft to the outside scene.

Abstract: A through connector device is disclosed. The device may include a coaxial cable receiver portion defined by one or more surfaces, the coaxial cable receiver portion configured to couple to a center conductor portion of a coaxial cable, the center conductor portion of the coaxial cable protruding above a dielectric material of the coaxial cable. The device may include a beam lead positioned adjacent to the coaxial cable receiver portion. The device may include a planar transmission line contact pad configured to make electrical contact with a planar transmission line of a printed circuit board. The device may include a step configured to electrically and mechanically couple the beam lead to the planar transmission line contact pad, the step configured to create a gap between a bottom surface of the beam lead and a top surface of an outer conductor portion of the coaxial cable.