Abstract: A flight management system includes a display for displaying a user interface and a processor coupled with the display and configured to receive flight plan information regarding a flight plan of an aircraft and aircraft status information from an aircraft monitoring system. The processor generates an alert indicating a deviation from the flight plan based on a comparison of the aircraft status information to the flight plan information, and provides the alert on a portion of the user interface displaying information indicative of the aircraft status information. The alert provides one or more user interface controls configured to enable a pilot to interact with the portion of the user interface displaying the information indicative of the aircraft status information to at least one of view additional information regarding the difference between the status information and the flight plan information and modify the flight plan of the aircraft.

Abstract: A high availability aircraft network architecture incorporating smart points of presence (SPoP) is disclosed. In embodiments, the network architecture divides the aircraft into districts, or physical subdivisions. Each district includes one or more mission systems (MS) smart network access point (SNAP) devices for connecting MS components and devices located within its district to the MS network. Similarly, each district includes one or more air vehicle systems (AVS) SNAP devices for connecting AVS components and devices within the district to the AVS network. The AVS network may remain in a star or hub-and-spoke topology, while the MS network may be configured in a ring or mesh topology. Selected MS and AVS SNAP devices may be connected to each other via guarded network bridges to securely interconnect the MS and AVS networks.

Abstract: A smart network access point (SNAP) device is disclosed. In embodiments, the SNAP device includes trunk ports for accepting a network trunk cable (e.g., fiber optic trunk) and thereby connecting the SNAP device to an aircraft-based network of SNAP devices. The SNAP device includes switch ports for incorporating physical connections to mission systems (MS) or air vehicle systems (AVS) components and devices, providing a local smart point of presence (SPoP) throughout a physical subdivision (e.g., network district) of an aircraft. The SNAP device is configured for monitoring data exchanges between local MS/AVS components and the aircraft network. The SNAP device includes a cybersecurity module for connecting to local security components (e.g., data guards and multiple levels of security (MLS) encryption/decryption) or for providing built-in data guard and encryption/decryption services. The SNAP device includes power control components for managing power distribution to the connected local network components.

Abstract: An aircraft, a system, and a method. The aircraft may include a computing device. The computing device may include a processor. The processor may be configured to utilize inertial navigation data, global navigation satellite system (GNSS) measurements, and flight trajectory data to compute navigation data and a predicted horizontal integrity level (HIL). The processor may be further configured to output the navigation data and the predicted HIL to be used for performance of a required navigation performance (RNP) procedure or a preflight planning procedure.

Abstract: A system may include a display and a processor communicatively coupled to the display. The processor may be implemented as a neural network. The processor may be configured to: receive image data associated with a location; receive geo-specific data associated with the location; use the image data and the geo-specific data to generate a photo-realistic image, wherein the photo-realistic image contains photo-typical content in geographically correct locations, wherein the photo-typical content appears typical for the location based at least on the geo-specific data; and output the photo-realistic image to the display for presentation to a user.

Abstract: A passenger rest cabin situated in the overhead crown area of an aircraft provides individual rest compartments along either lateral side of a central longitudinal corridor of limited height. The corridor and entrance thereto is configured to minimize the risk of claustrophobia by providing sensory preparation systems and techniques. Sensory preparation including transitional compartments with variations in video, lighting and ventilation are presented to the passenger to create a more inviting space. The limited height corridor is equipped with a series of handholds, sized and spaced according to the size of the average passenger, to mitigate the strain of traversing the corridor in a bent over position.

Abstract: A double data rate (DDR) RF digitization module for a software defined radio (SDR) is disclosed. In embodiments, the DDR RF digitization module includes a printed circuit board (PCB) terminating in a DDR memory bus interface comprising a plurality of input/output (I/O) connectors insertable into a DDR slot of an SDR motherboard. The RF digitization module is connectable to an RF front end of the SDR via receiver-side (Rx) and transmitter-side (Tx) RF connectors. The RF digitization module includes DDR analog-digital converters (ADC) and digital-analog converters (DAC) mounted to the PCB and in communication with the RF front end and the DDR memory bus. The DDR ADCs provide high speed digital sampling of inbound RF signals for the signal processors via the DDR memory bus, and the DDR DACs provide high speed generation of transmittable analog RF signals based on digital spectrum data generated by the signal processors.

Abstract: A system and method are disclosed for design of a suite of multispectral (MS) sensors and processing of enhanced data streams produced by the sensors for autonomous aircraft flight. The suite of MS sensors is specifically configured to produce data streams for processing by an autonomous aircraft object identification and positioning system processor. Multiple, diverse MS sensors image naturally occurring, or artificial features (towers buildings etc.) and produce data streams containing details which are routinely processed by the object identification and positioning system yet would be unrecognizable to a human pilot. The object identification and positioning system correlates MS sensor output with a-priori information stored onboard to determine position and trajectory of the autonomous aircraft. Once position and trajectory are known, the object identification and positioning system sends the data to the autonomous aircraft flight management system for autopilot control of the autonomous aircraft.

Abstract: Systems and methods for providing decision support guidance are provided. A method includes receiving airport information that includes a location of each airport of a plurality of airports. The method further includes determining a flight range of an ownship based on a location of the ownship and an amount of fuel remaining in the ownship, and determining if any airport of the plurality of airports is within the flight range of the ownship. The method further includes, for each airport within the flight range: determining an amount of time the ownship can maintain a current flight course before the airport is no longer within the flight range; and providing display data. The display data indicates the amount of time the ownship can maintain the current flight course before the airport is no longer within the flight range.

Abstract: A graphical depiction of insufficient system integrity for low-visibility synthetic vision system taxi mode is disclosed. The graphical depiction may be configured to be displayed on a display device of an aircraft. The graphical depiction may include an aircraft ownship symbol. The aircraft ownship symbol may be modified following a receipt of one or more signals related to a location of the aircraft relative to an aircraft movement surface and a comparison to the one or more signals to one or more thresholds. The comparison may be configured to determine whether there is insufficient system integrity in a degree of confidence in the location of the aircraft relative to the airport movement surface.

Abstract: A system and a method. The system may include a computing device configured for monitoring delay across clock domains using a dynamic phase shift. The computing device may be further configured to: use a counter value of a counter, a known primary clock period of a primary clock domain, a known secondary clock period of a secondary clock domain, and a current phase shift between a secondary clock and a phase shifted secondary clock to calculate a current offset between a last rising edge of the primary clock and a current rising edge of the secondary clock.

Abstract: A first waveguide of the HUD includes a first input coupler and a first output coupler. The first input coupler is configured to receive first light in a first bandwidth and provide the first light to the first output coupler. The first output coupler is configured to provide the first light in a first field of view. The first input coupler is configured to receive second light in a second bandwidth and provide the second light to the first output coupler. A second waveguide of the HUD includes a second input coupler and a second output coupler. The second input coupler is configured to receive third light in the first bandwidth and provide the third light to the second output coupler. The second output coupler is configured to provide the third light in the second field of view.

Abstract: A receiver apparatus and method for optimized decryption and despreading of a very low frequency (VLF) bitstream is disclosed. In embodiments, the receiver includes antenna elements for receiving a transmission security (TRANSEC) encoded bitstream associated with an uncertainty window size and a spread factor. The receiver includes cryptographic processors that, when the spread factor is sufficiently large, select key section numbers A and data section numbers B based on the window size and spread factor. The cryptographic processors generate an output sequence of correlation windows, each correlation window associated with a symbol of the bitstream, via pipelined sectional mirrored-key convolution based on a key section number A and data section number B chosen to optimize performance (e.g., processor performance, memory performance).

Abstract: In an illustrative embodiment, a control system to synchronize a number of slave fans to a master fan may include a master voltage controlled oscillator to receive input voltages, rotate master blades of the master fan pursuant to the input voltages, and provide reference synchronization signals; a slave voltage controlled oscillator to receive the input voltages modified by a gain, rotate slave blades of the slave fan at slave fan speed pursuant to the input voltages, and provide slave synchronization signals; and a phase lock loop configured to receive the reference synchronization signals and the slave synchronization signals, provide a comparison between the reference slave synchronization signals, and provide the gain pursuant to the comparison between the reference synchronization signals and the slave synchronization signals.

Abstract: A system may include a fastener strap, a first component, and a second component. The fastener strap may include a strap section, at least one first stiffening rib section, and at least one second stiffening rib section. The first component may include a first strap section channel and at least one first stiffening rib section channel positioned along the first strap section channel. The second component may include a second strap section channel and at least one second stiffening rib section channel positioned along the second strap section channel. When the fastener strap is installed in the first strap section channel, the at least one first stiffening rib section channel, the second strap section channel, and the at least one second stiffening rib section channel, a load-bearing connection may be formed between the first component and the second component.

Abstract: A circuit card assembly (CCA) is disclosed. In embodiments, the CCA includes a printed circuit board (PCB) comprising a series of adjacent substrate layers. Evaporator layers include an evaporator surface thermally connected to CCA components and capable of absorbing heat therefrom. A series of wall layers include apertures collectively defining an integrated vapor chamber extending between the evaporator layers and condenser layers including a condenser surface opposite the evaporator surface. A working fluid within the vapor chamber is boiled by heat transferred from the evaporator surface and re-condenses at the condenser surface, which transfers heat from the working fluid. The re-condensed working fluid is transitioned back to the evaporator surface via capillary wick structures within the internal surfaces of vapor chamber.

Abstract: A system and related method operates to receive autopilot selection and monitor aircraft systems to control which autopilot is actively flying the aircraft. During certain flight operations in which a single autopilot is in use, the system reverts to the next available autopilot should the active and selected autopilot disconnect for any reason (e.g., faults and/or failures). The system maintains a redundant ability for pilot use of each pilot selectable mode of each autopilot channel including altitude hold, speed hold, heading hold, etc. For an indication to a pilot or remote operator that the system has reverted to a second autopilot, the system commands a momentary aural warning and a visual message/lights. For failures resulting in timely but necessary maneuver requirements, the system maintains autopilot control laws, control authority and roll authority.

Abstract: The antenna includes a substrate and a plurality of unit cells coupled to the substrate. Each unit cell includes a dipole feed extending from the substrate, a first antenna dipole coupled to the dipole feed, and a second antenna dipole coupled to the dipole feed. The first antenna dipole includes a first arm on a first side of the dipole feed and a second arm on a second side of the dipole feed opposite the first side. The second antenna dipole includes a third arm on a third side of the dipole feed and a fourth arm on a fourth side of the dipole feed opposite the third side.

Abstract: An aircraft communication system includes, and a method of aircraft communication uses, communication radios and a multilink communication controller. The multilink communication controller includes a link selection table and a link selector. The link selector is in communication with the link selection table. The link selector is configured to receive a message from a system of the aircraft and select a communication link among a number of communication links for the message using a priority of the message and priority information from the link selection table.