Abstract: A resistive touch sensor includes a base layer, a sensor top sheet positioned in spaced apart relation to a base layer, and a peripheral edge seal formed between the sensor top sheet and the base layer. The sensor further includes a first adhesive layer bonded on a peripheral edge portion to the sensor top sheet, and a second adhesive layer, inset relative to the peripheral edge seal, positioned between the first adhesive layer and the sensor top sheet. The second adhesive layer is bonded on one side to the first adhesive layer and an opposing side to the sensor top sheet corresponding to a portion of a touch active area. The second adhesive layer causes a planarity change in the sensor top sheet proximate the peripheral edge seal thereby increasing the usable area and improving uniformity of touch force across the sensor.

Abstract: A system and method for inferring operator intent by detecting operator focus incorporates cameras positioned within a cockpit or control space of a vehicle and oriented at an operator of the vehicle. The cameras capture images of the operator in a control seat; the images are analyzed (either individually or sequentially) to determine a gaze and/or body pose of the operator (including, e.g., a position and orientation of the torso and limbs). By comparing the determined gaze and/or body pose to the positions and orientations of potential focus targets within the control space (e.g., windows, display units, and/or control panels that the operator may engage with visually and/or physically), the system predicts the most likely future focus target or targets: what the operator is most likely to visually and/or physically engage with next. Operator intent may be further analyzed to identify potentially abnormal or anomalous behavior.

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 a portion including textual characters, wherein each textual character of the textual characters is formed of line segments; 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 size of the at least one file is smaller than the graphical image file.

Abstract: A system and method for a multi-panel multi-function active electronically scanned array (AESA) radar operation receives radar commands from individual aircraft systems and segments a plurality of AESA panels fixed (at variable azimuth/elevation about the aircraft) into a plurality of subarrays to carry out each individual function commanded by the individual aircraft system. Dependent on aircraft status and phase of flight, the and individual AESA are designated for use and the subarrays are sized based on desired radar function at the specific phase of flight and specific threat associated with the phase. The system dynamically shifts the designated AESA, subarray size, beam characteristics, power settings, and function to enable multiple simultaneous function of the suite of AESA panels.

Abstract: A radar system receives threat relevant data with pulses sufficiently separated to provide sufficient long-range imaging, analyzes the return data to identify features of the threat, and generate a second set of pulses to acquire more detailed, higher granularity data specific to the threat. The system may include an ESA that is configured for pulses in a higher frequency to acquire higher resolution data specific to the threat.

Abstract: A system may include a user interface and a processor. The processor may be configured to (a) pre-arm multiple actions according to a conditional timeline and any associated trigger events, and (b) output commands to cause the multiple actions to be completed at times consistent with the conditional timeline and any associated trigger events.

Abstract: According to various embodiments, a biomedically actuated occupant restraint system includes an occupant restraint system for a vehicle, the occupant restraint system having a locked position and an unlocked position. The biomedically actuated occupant restraint system further includes an occupant monitoring system operably connected to the occupant restraint system, the occupant monitoring system configured for monitoring a plurality of physiological conditions of an occupant of the vehicle. The occupant monitoring system includes a biometric sensor module including a plurality of physiological sensors configured for measuring a plurality of physiological conditions of the occupant and asserting a plurality of sensor signals, and a controller configured to receive the plurality of sensor signals and determine whether the occupant is incapacitated. The controller being configured to send a command to lock the occupant restraint system in response to determining the occupant is incapacitated.

Abstract: A system may include an optical phased array, a photodiode array, and a radiofrequency (RF) antenna element array. The optical phased array may be configured to: receive a laser signal from a signal laser; and output an optical beam. Each photodiode may be configured to: receive at least a portion of the optical beam and at least a portion of an optical plane wave beam, wherein the optical plane wave beam is formed based at least on a local oscillator (LO) laser that outputs a laser beam having a different wavelength from the signal laser; and output an electronic signal based on the at least the portion of the optical beam and the at least a portion of the optical plane wave beam. The RF antenna element array may be configured to output an RF beam based on received electronic signals from the photodiode array.

Abstract: An integrated circuit (IC) package comprises a substrate having an outer portion close to the perimeter of the substrate, an inner portion surrounded by the outer portion, and an upper surface incorporating a wiring layer for the bonding of a semiconducting die (e.g., via its bottom face). The IC package includes a metallic or otherwise thermally conductive heat spreader thermally bonded on an inner surface of a boss on its bottom side to the top surface of the semiconducting die, and extending on its top surface to the edges of the substrate to maximize heat dissipation from the die. The boss extends toward the semiconducting die and is thermally coupled to the top face of the semiconducting die.

Abstract: A system and method for automation of flight functions across an aircraft cockpit provides an open systems architecture to meet next generation mission capabilities for increased aircrew effectiveness. A mission reasoner (MR) receives inputs from a vehicle health system, mission phase analysis, and external assets (wingmen) to build a decision network based on a knowledge database providing a decision aid to automate flight functions across the cockpit. The MR reduces crew workload by providing an automated decision aid and increased situational awareness of own ship aircraft and cooperating nearby vehicle health status relating to a phase of mission success. The MR provides predictive decisions and alternative actions to complete one or more desired mission objectives and determines predictive maintenance and future failures to optimize condition-based maintenance and reduce cost.

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: A structural connector system for providing an electrical connection between electronic componentry is disclosed. The structural connector system includes a structural member, including an electrically insulating matrix, an electrically conducting path, a first end surface, a second end surface, and a first component engaging surface. The first component engaging surface includes a first mechanical coupler configured to mechanically couple a first electronic component or a first chassis component to the structural member and a first electrical coupler configured to electrically couple the first electronic component or the first chassis component to a first end of the electrically conducting path.

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 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 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 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 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 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 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.