Abstract: In one embodiment, an electronic display assembly includes a sensor array located on one side of a circuit board and an electronic display array located on an opposite side of the circuit board from the sensor array. The sensor array includes a plurality of sensor pixel units. Each sensor pixel unit includes a plurality of sensor pixels. The electronic display array includes a plurality of display pixel units. Each display pixel unit includes a plurality of display pixels. Each particular one of the plurality of sensor pixel units is mapped to a corresponding one of the plurality of display pixel units such that display pixels of each particular one of the plurality of display pixel units display light corresponding to light captured by sensor pixels of its mapped sensor pixel unit.

Abstract: A system includes a printed circuit board (PCB). The PCB includes a radio frequency (RF) circuit that includes a plurality of circuit modules and signal trace lines. Each circuit module is electrically connected to at least one other circuit module by a signal trace line. The system includes a via fence comprising fence walls having at least two materials laminated using a printed wire board (PWB) process. The fence walls include a plurality of vias. The fence walls form a plurality of free-form RF isolation chambers, each chamber includes chamber walls that surround each circuit module outside of the PCB. The embodiments also include a method of manufacturing and/or isolating the system or components of the system.

Abstract: A method for preventing corona effects in an electronic circuit comprising applying a coating of a first material to a surface of the electronic circuit, and applying a second material having a dielectric constant that is lower than that of the first material on an exposed surface of the first material, wherein the second material comprises a solid dielectric.

Abstract: Systems and methods for detection and display of marine objects for an aircraft. One example system includes a transceiver configured to communicate with an Automatic Identification System (AIS) server and an electronic controller located within an aircraft. The electronic controller is configured to provide on a display an interface comprising a map representing a travel area. The electronic controller is configured to provide, on the map, a first graphical representation of the aircraft within the travel area. The electronic controller is configured to receive, via the transceiver, marine object data from the AIS server. The electronic controller is configured to periodically update, on the map, a second graphical representation of a first marine object within the travel area based on the marine object data.

Abstract: A communication system consists of a satellite constellation including a number of NGSO satellites, one or more gateways and a control center. The satellites facilitate communication for multiple user terminals. Each gateway communicates with the satellites and user terminals and provides connectivity to the terrestrial networks, and the control center controls operation of the satellites, the gateways and the user terminals. The satellites, the user terminals, the gateways and the control center include hardware that may be software-defined network (SDN) enabled to ensure efficient admission control, precision handover management and quality-of-service (QoS) enforcement algorithms.

Abstract: An aircraft includes an airframe defining a first enclosed space, an engine bay disposed within the first enclosed space, and a cooling system. The engine bay includes a firebox defining a second enclosed space and an engine disposed at least partially within the second enclosed space. The cooling system is configured to selectively fluidly couple the first enclosed space with the second enclosed space.

Abstract: A technique relates to autonomous obstacle avoidance. A vehicle is controlled on a route to a destination, the route being a three-dimensional route. An obstruction is determined on the global route. A local route including alternate points to avoid the obstruction is autonomously determined. The local route is autonomously converged back to the global route in response to avoiding the obstruction.

Abstract: A replacement tip section for a rotor blade, from which a legacy tip section was removed, includes a blade tip portion configured to be attached to an intermediate section of the rotor blade after removal of the legacy section. The intermediate section has a connection feature at an end of the intermediate section to which the blade tip portion is attachable. The replacement tip section includes a transition region configured to be attached to a forward end of the connection feature. The transition region is configured to form a leading edge of the rotor blade and extends from the blade tip portion to form an opening into which the intermediate section is attached. The transition region includes a first end having a first airfoil that conforms to the intermediate section airfoil at the connection feature, and a second end having a second airfoil that conforms to the blade tip portion.

Abstract: This disclosure relates to apparatuses, systems, and methods for handling faults on vehicles. One or more processors in a vehicle may receive, from a control unit in response to a detection of a fault in the vehicle, an indication of a degradation in a performance constraint of the vehicle. The processors may determine, responsive to the degradation in the performance constraint, that the vehicle is unable to execute a set of commands to control a movement of the vehicle along a trajectory. The processors may generate, in accordance with the degradation in the performance constraint, a modified set of commands that the vehicle is able to execute to control the movement of the vehicle along at least a portion of one or more trajectories. The processors may provide the modified set of commands to the control unit of the vehicle to control the movement of the vehicle.

Abstract: A photonic integrated circuit (PIC)-based imager blade includes a number of PIC imager units stacked on top of one another. Each PIC imager unit includes a PIC coupled, at a first end and a second end, to a first set of lenslets and a second set of lenslets, respectively. An electronic integrated circuit (EIC) is coupled to the PIC. Pairs of lenslets of the first and second set of lenslets are optically coupled to respective waveguides embedded in the PIC. The PIC imager units have different lengths, and longer PIC imager units include larger lenslets.

Abstract: A power display of an aircraft having a main rotor system and a translational thrust includes a reference member, a first indicator arranged adjacent the reference member and operable to display a power being used by the main rotor system, and a second indicator arranged adjacent the reference member and operable to display a power being used by the translational thrust system.

Abstract: An apparatus for securing first and second skins to a core in a composite rotor blade includes an elongated member configured to be installed through a passage in the core of the composite rotor blade. The elongated member has a first end configured to be attached to an outer surface of the first skin and a second end configured to be attached to an outer surface of the second skin. The apparatus also includes a first patch configured to adhere the first end to the outer surface of the first skin, and a second patch configured to adhere the second end to the outer surface of the second skin such the elongated member extends from the outer surfaces of the first and second skins through the passage in the core.

Abstract: According to an aspect, a pivoting sail fairing system includes a rotatable fairing, for rotation about a first axis of rotation of an aircraft, that includes a housing that defines a compartment arranged inward from the housing, the housing including a first orifice on a first surface and a second orifice on a second surface of the housing, and a first actuator mounted on a surface of the compartment inward from the housing.

Abstract: An apparatus comprising a stack of printed circuit board (PCB) layers having a primary longitudinal structure forming a radio frequency (RE) via including a principal tuning section (223) and a constant longitudinal structure (227) along a conductive column support (255) journaled through the layers in the via. The principal section (221) comprising a first tuning sub-assembly (229 A) in a first portion of the RE via above the longitudinal structure (227) and at an entrance of the primary longitudinal structure (221) and comprising a first set of pad, anti-pad pairs (445, 545, 645) tuned to receive an RE band. A second principal tuning sub-assembly (229B) in a second portion of the via below the longitudinal structure (227) and at an exit of the primary longitudinal structure and comprising a second set of pad, anti-pad pairs (445, 545, 645) tuned to receive the band and mirroring the first set of pairs.

Abstract: An adjustable control link for transferring rotor shaft rotation to a rotating swashplate, the adjustable control link includes an elongate element rotatable with the rotor shaft, the elongate element having a first end. A structure has an opening and a second end. At least one cam component is disposed within the opening and is rotatable relative to the structure about a central axis of the opening. A pin is configured to couple the elongate element to the at least one cam component. The pin is eccentrically rotatable about the central axis to move the first end of the elongate element relative to the second end of the structure.

Abstract: A wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side. The second side includes a plurality of vortex generators arranged in an array configuration. The vortex generators generate one or more vane vortices near an end of the low pressure side of the wing, thereby weakening a wingtip vortex generated by the wing.

Abstract: An aircraft and a control yoke for operating the aircraft. The control yoke includes a base, a handle for manual operation of the aircraft, and a graphical communication device centered at the base for receiving a command from an operator and autonomously operating the aircraft according to the received command.

Abstract: In an embodiment, a system includes a three-dimensional (3D) printer, a neutral feedstock, a p-doped feedstock, an n-doped feedstock, and a laser. The 3D printer includes a platen and an enclosure. The platen includes an inert metal. The enclosure includes an inert atmosphere. The neutral feedstock is configured to be deposited onto the platen. The neutral feedstock includes a halogenated solution and a nanoparticle having a negative electron affinity. The p-doped feedstock is configured to be deposited onto the platen. The p-doped feedstock includes a boronated compound introduced to the neutral feedstock. The n-doped feedstock is configured to be deposited onto the platen. The n-doped feedstock includes a phosphorous compound introduced to the neutral feedstock. The laser is configured to induce the nanoparticle to emit solvated electrons into the halogenated solution to form, by reduction, layers of a ceramic comprising a neutral layer, a p-doped layer, and an n-doped layer.

Abstract: Systems and methods for mission-based path modifications are presented herein. One or more processors may be coupled with memory and housed in a vehicle. The one or more processors may receive data indicative of an issue with at least one function of the vehicle during a mission defined by a type of cargo and a flight path comprising a plurality of segments. The one or more processors may determine, responsive to the issue with the at least one function, an action to perform for the vehicle based on the issue, a current segment of the plurality of segments, and the mission. The one or more processors may execute, during the current segment or a subsequent segment of the plurality of segments, the action on the vehicle.

Abstract: A distributed power amplifier includes radio frequency (RF) input and output terminals. A first field effect transistor (FET) is coupled at a first gate terminal to the RF input terminal and at a first drain terminal to the RF output terminal. The first FET has a first periphery and a first source terminal electrically connected to ground potential. A second FET has a second periphery smaller than the first periphery. The second FET has a second gate terminal electrically coupled to the first gate terminal through a first inductor, a second drain terminal electrically coupled to the first drain terminal through a second inductor, and a second source terminal electrically connected to the ground potential. A drain voltage terminal, which excludes a resistive element, is electrically coupled to a drain bias network through which a drain bias voltage is applied to the first drain terminal and the second drain terminal.