Abstract: A system and method for offloading Future Air Navigation System (FANS) and Automated Dependent Surveillance-Contract (ADS-C) functionality from the flight management system (FMS) to an aircraft-based communications management unit (CMU) receives intent data outputs from the FMS, each intent data output including aircraft state and trajectory intent data. Based on the received intent data outputs, the CMU generates a dynamic route representation approximating the aircraft route, inferring and connecting waypoints without otherwise querying the FMS or the pilot for additional data. The CMU receives inbound messages related to ADS-C contracts established with the aircraft by air traffic control (ATC) ground stations and, based on the dynamic route, generates and transmits any necessary ADS-C reports to the ATC ground stations. Further, the CMU queries aircraft-based absolute and relative navigational systems to verify navigational system availability and accuracy status with each ADS-C report.

Abstract: An ESA includes radiating elements having a normal mode radiating element and a superimposed end-fire mode radiating element. The combined normal mode radiating element and and-fire mode radiating element attenuators or variable gain amplifiers for amplitude adjustment, phase shifting, and time delay circuitry and algorithms to drive the normal mode radiating element and end-fire mode radiating element simultaneously to produce radiation patterns that constructively interfere. Alternatively, the radiating elements are fed by a radio frequency (RF) feed and switching integrated circuitry timed to drive the normal mode radiating element and end-fire mode radiating element to effectively produce hemispherical radiation patterns as a function or time/scan angle.

Abstract: A radar system including an AESA illuminates a target with a first pulse for a desired beam pointing angle (azimuth and elevation). The AESA then illuminates the target with a second pulse for the desired pointing angle, the second pulse defining a radiation pattern with a main beam in phase with the first pulse, but side lobes that are out of phase. The radar system receives return signals and combines the return signals to null the side lobes by the principle of superposition. The radar processing unit is time synced such that the pulse-pair is interpreted as a single ultra-low level side lobe return radiation pattern.

Abstract: A method for heads-up control and interactive display of traffic targets via a heads-up display (HUD) includes: receiving position data from proximate aircraft (e.g., within a threshold range); arranging the aircraft into an ordered sequence based on proximity or other criteria; overlaying interactive symbology onto the HUD synthetic display corresponding to the proximate aircraft (including any aircraft within range but outside the HUD field of view, e.g., behind the aircraft or pilot); accepting control input from a user via a heads-up controller (e.g., manual control or voice command) and focusing a cursor on each proximate aircraft in sequence based on the control input; selecting, via the heads-up controller, focused aircraft via the heads-up controller; and designating, via the heads-up controller, selected aircraft for CDTI Assisted Visual Separation (CAVS) or other traffic applications.

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 method for correlating a first item to a second item is disclosed. The method includes detecting a first identifier associated with the first item and detecting a second identifier associated with the second item. The method further includes simplifying the first identifier, and executing a matching procedure configured to match the first identifier to the second identifier and generating a match value, which includes comparing the first identifier to the second identifier and generating the match value between the first identifier and the second identifier. The method also includes reporting a correlation between the first item and the second item based on the match value. The method may be performed by a system that includes a controller, one or more processors, and memory.

Abstract: Neutron single effect events are mitigated using gadolinium. Layers of gadolinium are fully encapsulated as part of an airborne electronic hardware, in circuit boards, in heat sinks, and as part of the device packaging. The gadolinium layers are designed to shield semiconductor chips from neutrons. Shielding the semiconductor chips from the neutrons reduces the upset rate of device packages using the semiconductor ships.

Abstract: A system includes a head-up display (HUD) system including a display; a combiner; and at least one processor communicatively coupled to at least one image sensor of at least one tracking system and to the display. The at least one processor configured to: receive image data from one or more of the at least one image sensor, wherein the image data is (i) for performing eye tracking and/or head tracking operations and (ii) for monitoring the displayed images; and detect the at least one malfunction of the HUD system.

Abstract: A system may include a display and a processor communicatively coupled to the display. The processor may be configured to: output, to the display, a view of an airport moving map (AMM); receive aircraft state data and airport surface data; at least based on the current position of the aircraft and at least one factor, obtain commonly used taxi route data from a data structure, the data structure including taxi route data, the taxi route data including information of commonly used taxi routes for the airport, wherein the commonly used taxi route data includes information of a commonly used taxi route for the aircraft on the airport surface; based at least on the commonly used taxi route data, the aircraft state data, and the airport surface data, generate taxi routing guidance content; and output, to the display, the taxi routing guidance content.

Abstract: A capacitor bank includes a printed circuit board adapted for a first capacitor disposed on a first surface of the printed circuit board and a second capacitor disposed on a second, opposing surface of the printed circuit board. The first and second capacitor are connected to the printed circuit board at surface mounts pads on opposing sides of the printed circuit board that may be in electronic communication with each other. The capacitors may be connected in series or parallel. Multiple printed circuit boards with capacitors on opposing surfaces may include flexible printed circuit board portions to allow the capacitor bank to be folded into an available space.

Abstract: A system may include a processor, a night vision sensor, and an objective lens assembly comprising four lenses. Each of a first lens, a second lens, a third lens, and a fourth lens may be configured to project a real world scene onto one of four portions of the night vision sensor. The night vision sensor may be configured to provide four images of the real world scene from the objective lens assembly to the processor. The processor may be configured to: receive a first image, a second image, a third image, and a fourth image from the night vision sensor; generate color night vision image data based at least on the first image, the second image, the third image, and the fourth image; and output the color night vision image data.

Abstract: A system and method for interference detection. The system and method receives flight data comprising a plurality of flights. The system and method identifies a plurality of signal drop events based on at least the flight data. The system and method determines one or more co-located signal drop event subsets based on at least the plurality of signal drop events and filter criteria. The system and method determines one or more interference events based on the one or more co-located signal drop event subsets, wherein each of the one or more co-located signal drop event subsets is based on at least two or more of the plurality of signal drop events.

Abstract: A supply glider is disclosed herein. The supply glider includes a body having a first end and a second end, the body being configured to be coupled to a host aircraft, a container disposed between the first end and the second end of the body, wings coupled to the body between the first end and the second end, and stabilators coupled to the body adjacent the second end.

Abstract: A method for determining performance of an imaging device in real-time is disclosed. The method may include, but is not limited to, receiving a first set of images of a first calibration target positioned at a first position from one or more imaging devices, determining a first environmental condition external to the aircraft at the first position based on the received first set of images using a machine learning algorithm; receiving additional set of images of an additional calibration target positioned at an additional position from the one or more imaging devices; determining an additional environmental condition external to the aircraft at the additional position based on the received additional set of images; and determining one or more real-time calibration parameters for the one or more imaging devices based on at least one of the determined first environmental condition and the determined additional environment condition.

Abstract: A status information management system correlates checklist data from all stored checklists to create a holistic, function level representation of aircraft health. Components are associated with defined function level categories. When a component fault is detected, the contextual information management system identifies each function level category that includes that component, and flags that function level category as having a fault. Such flags may be represented on a display where each function level category is displayed. A flight crew member selecting the function level category may see all systems impacted by the component fault. When selecting a function level category, the information management system may render a graphical depiction of the aircraft and the systems included in the function level category. The component fault may be depicted along with an impact criticality to the rendered systems.

Abstract: An ejection system is disclosed herein. The ejection system includes a seat having a seat bucket and a seat back, a passive head and neck protection device coupled to the seat back, and an ejection initiation system. The ejection initiation system includes a pull handle coupled to the seat bucket, a first connector having a first end coupled to the pull handle, an ejection sequence initiation device configured to initiate an ejection sequence, a passive head and neck protection mechanism configured to activate the passive head and neck protection device, and an ejection pull connector having a first end and a second end, the second end coupled to the ejection sequence initiation device and to the passive head and neck protection mechanism.

Abstract: A contact-less check-in system is disclosed. The system includes a kiosk that includes a housing, a display, and a communication module. The system further includes one or more processors and a memory with instructions stored within instructing the kiosk to receive input signals from a user device, transmit display signals to the display based on the input signals, and perform one or more business functions based on the input signals. The communication module may be configured to communicate with the user device via IEEE 802 protocols or infrared signals. A method to convert a contact-required check-in system to a contact-less check-in system in also disclosed.

Abstract: A system and method for correlating a received signal is disclosed. The system may include an antenna configured to receive the received signal. The system may also include a controller. The controller may include a field programmable gate array (FPGA) including a plurality of look-up tables (LUTs). The controller may also include a plurality of registers for storing and manipulating data. The plurality of registers may be coupled to the plurality of LUTs. The plurality of registers may include a known reference register, a secondary reference register, an in-phase register, and a quadrature register. Each LUT may be configured to receive Boolean inputs from the known reference register, the secondary reference register, the in-phase register, and the quadrature register and to output correlation results based on the Boolean inputs.

Abstract: A system may include a transmitter node and a receiver node. Each node may include a communications interface including at least one antenna element and a controller operatively coupled to the communications interface, the controller including one or more processors, wherein the controller of the receiver node has information of own node velocity and own node orientation. The receiver node may be in motion and the transmitter node may be stationary. Each node may be time synchronized to apply Doppler corrections associated with said node's own motions relative to a common reference frame. The common reference frame may be known to the transmitter node and the receiver node prior to the transmitter node transmitting signals to the receiver node and prior to the receiver node receiving the signals from the transmitter node.

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.