Abstract: A gear box includes a housing, an actuator coupled to the housing, and a bearing assembly pivotably coupled to the actuator. The bearing assembly including an outer raceway, a cylindrical housing positioned within the outer raceway, and an annular bearing positioned between the outer raceway and the housing. The cylindrical housing has a first end and a second end opposite the first end. A sensor is coupled to the first end of the cylindrical housing and configured to monitor an operating condition of the annular bearing. A linkage couples the actuator to the second end of the cylindrical housing and an output shaft is rotatably coupled to the bearing assembly.

Abstract: A circuit assembly includes a sealable enclosure and at least one electronic circuit element contained within the sealable enclosure. The at least one electronic circuit element includes a control circuit, a garnet, and a first polymer material applied on a surface of the control circuit and on a surface of the garnet. A second polymer material fills a remaining space defined within the enclosure, the second polymer material applied on an exposed surface of the first material.

Abstract: In one embodiment, systems and methods include using an inspection and projection system to measure the thickness of a coating and provide visual guidance for secondary operations. The inspection and projection system comprises a robotic arm operable to rotate about a plurality of axes, wherein an end effector is disposed at a distal end of the robotic arm. The inspection and projection system further comprises a linear rail system, wherein the robotic arm is coupled to the linear rail system, and wherein the robotic arm is operable to translate along the linear rail system. The inspection and projection system further comprises a frame, wherein the linear rail system is disposed on top of the frame, and an information handling system coupled to the frame, wherein the information handling system is operable to actuate the robotic arm and the linear rail system.

Abstract: A method of manufacturing an electrical circuit from bulk materials includes the steps of machining a first bulk dielectric material, forming a conductive element, and placing the conductive element on a first side the first bulk dielectric material. The method further includes the step of machining a second bulk dielectric material and placing the second bulk dielectric material on the first side of the first bulk dielectric material and over the conductive element. The first bulk dielectric material and the second bulk dielectric material may be laminated together.

Abstract: An aircraft includes a main body having an empennage, a main rotor assembly mounted on the main body, and a movable control surface assembly supported on the empennage. The movable control surface assembly includes a tube extending from the empennage along a tube axis to a free end, the tube being supported for rotation about the tube axis with respect to the empennage, and a movable control surface mounted on the tube for rotation therewith. The movable control surface is supported on the tube by a connection element that couples the movable control surface to the free end of the tube to rotatably fix the movable control surface with respect to the tube.

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: According to an aspect, a method of assembling a mandrel includes assembling a plurality of members via interlocking features arranged at opposing edges of each member of the plurality of members to form a compartment, the assembled members having a collective outer surface that conforms to an inner surface of the spar. A support member is inserted into the compartment formed radially inward from the assembled members, the support member making contact with a portion of each member of the plurality of members.

Abstract: Provided herein are various enhancements for antenna systems and directed radio frequency energy structures. In one example, an apparatus includes an antenna array comprising a plurality of antenna elements formed by waveguide structures embedded within a substrate and positioned about a longitudinal axis of the substrate to form at least two concentric ring arrangements of antenna elements. Apertures of the waveguide structures are configured to emit or receive radio frequency (RF) energy generally along the longitudinal axis. Feed elements are coupled to each of the waveguide structures on an end opposite of the apertures, and configured to couple the RF energy for the antenna array.

Abstract: Load volume predication for slung loads of aerial vehicles are disclosed. A system can identify parameters of a load. The system can determine a volume occupied by a superposition of locations of the cone. The system can receive from sensors or models, characteristics of an environment associated with the aerial vehicle or the load. The system can detect an obstacle in the environment. The system can take a navigational action in response to detecting the obstacle.

Abstract: Offline task-based feature processing for aerial vehicles is provided. A system can extract features from a world model generated using sensor information captured by sensors mounted on an aerial vehicle. The system generates a label for each of the features and identifies identify processing levels based on the features. The system selects a processing level for each feature of a subset of features based on a task performed by the aerial vehicle and the label associated with the feature. The system generates one or more processed features by applying the processing level to a respective feature of the subset of the plurality of features. The system presents the one or more processed features on a display device of the aerial vehicle.

Abstract: A load control unit includes a first input terminal configured to receive power, a second input terminal configured to receive load information, a first output terminal configured to provide a first portion of the power to a first load, a second output terminal configured to provide a second portion of the power to a second load, a memory, and an electronic processor communicatively connected to the memory, first input terminal, the second input terminal, the first output terminal, and the second output terminal. The electronic processor is configured to measure the power received via the first input terminal, receive load parameters via the second input terminal, and dynamically control, in response to measuring the power and receiving the load parameters, at least one of the first load or the second load based on the power that is measured and the load parameters that are received.

Abstract: In one embodiment, systems and methods include using an automated laser system to remove a portion of a coating for nutplate installation. An automated laser system comprises a laser scanner and a laser head, wherein the laser head is coupled to the laser scanner. The laser head comprises a containment unit and a vacuum connector wherein the vacuum connector is disposed on a first side of the containment unit. The laser head further comprises a camera system, a light source, a first actuator, and a second actuator all disposed on a top surface of the containment unit. The laser head further comprises an end piece, wherein the second actuator is configured to displace the end piece.

Abstract: A method of modifying a rotor blade is provided for a rotor blade including a spar having an inboard portion with a substantially constant overall height, the inboard portion further including a top layer having a substantially constant first thickness and a bottom layer having a substantially constant second thickness. The method includes removing a root portion of the inboard portion to thereby modify the rotor blade and installing a cuff configured to couple to the rotor blade to an aircraft.

Abstract: A rotor blade for a rotary wing aircraft includes a leading edge and a trailing edge defining a chordwise direction. The leading edge defines a forward end of the rotor blade and the trailing edge defines an aft end of the rotor blade. The rotor blade has a center of gravity and an aerodynamic center along the chordwise direction. The center of gravity is aft of the aerodynamic center.

Abstract: A hybrid propulsion system extracts electrical power using a combined heat engine and electrical generator. The propulsion system includes a gas generator, an electrical power generator disposed upstream of the gas generator and configured to be driven by a power turbine, an output power shaft mated to the power turbine and extending through a central axis of the gas generator and power generator unit, an engine enclosure circumferentially surrounding the power generator, and a shroud disposed between the power generator and the engine enclosure. The electrical power generator includes at least one rotating member and a stationary conductive member, wherein the at least one rotating member includes a magnetic portion, and rotation of the at least one rotating member relative to stationary conductive member generates a current transmissible by one or more coupled power output cables.

Abstract: A vibration control assembly includes a housing having an interior region and an inner mass including a cage disposed within the interior region of the housing and being rotatable within the housing about a first axis and a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis. At least one driving source includes a stator and is operable to interact with a magnetic field of the inner mass to drive rotation of the inner mass about at least one of the first axis and the second axis, wherein the at least one driving source is mounted within the interior region of the housing.

Abstract: Provided herein are various enhanced systems, apparatuses, and techniques for on-surface analysis of celestial or terrestrial surfaces, such as for discovery and analysis of water ice deposits, locations, abundances, and depths. An example herein includes a swarm of spherical payloads sequentially deployed by a deployment host across a large area of a surface to impact the surface, sense properties of the surrounding environment using avionics and scientific instrumentation, and to establish a communication network to collect and transmit collected data.

Abstract: Provided herein are various magnetoelectric dipole antenna arrays and multi-array arrangements for handling radio frequency signals. In one example, an antenna array includes a baseplate conductively coupled to sets of plate elements by support members that position the plate elements at selected distances offset from a surface of the baseplate. Antenna probes are arranged in orthogonal pairs positioned within gaps between a corresponding set of plate elements, with each antenna probe comprising a conductive strip having a feed section coupled to a radio frequency connection through the baseplate, a transverse section generally parallel with the baseplate, and a terminal section directed back toward the baseplate. Dielectric structures for each pair of antenna probes comprise a dielectric material having channels that recess the conductive strips therein and a dielectric spacer positioned between overlapping transverse sections of the antenna probes.

Abstract: Provided herein are various improvements to antenna stabilization systems, such as employed on confocal phased array reflector antenna arrangements. In one example, a system includes a feed structure for a main reflector, the feed structure comprising an electronically scanned array (ESA) feed and a sub-reflector. The sub-reflector is configured to propagate a signal between the ESA feed and the main reflector. The system also includes a star tracker element coupled to the feed structure and configured to determine orientation information relative to star alignment, and laser distancing elements coupled to the feed structure and configured to determine distance measurements relative to the main reflector. A control system is configured to determine pointing errors of the main reflector based at least on the orientation information and the distance measurements, and these pointing errors can be used by the ESA feed to adjust steering of a signal towards a target.

Abstract: A heating system for a component within a compartment of a spacecraft includes a fuel source, a gas generator, and a heat sink. The fuel source includes hydrazine. The gas generator is in fluid communication with the fuel source. The gas generator includes a catalyst. The catalyst is configured to decompose the hydrazine and generate an exhaust gas. The heat sink is thermally coupled to the gas generator and configured to receive heat from the exhaust gas of the gas generator. The heat sink is thermally coupled to the component within the compartment of the spacecraft to transfer heat from the exhaust gas to the component.