Abstract: Systems and methods include a tilt device for an aircraft vehicle. The tilt device is configured to rotate a rotor assembly between first and second positions. The tilt device comprises a linear actuator disposed within an aircraft fairing; a sleeve having a slot defined therein; and a piston coupled to the linear actuator configured to translate axially within the sleeve. A method includes actuating the linear actuator to translate the piston, wherein the rotor assembly is coupled to an end of the piston and comprises a motor and one or more rotor blades. The method further includes rotating the piston within the sleeve as the piston translates axially along the sleeve via a pin disposed within a slot defined in the sleeve, wherein the pin extends from the piston and through the slot. The method further includes actuating the motor to operate the one or more rotor blades.

Abstract: Embodiments of the present disclosure provide an adjustable diameter step pin apparatus. The adjustable diameter step pin apparatus includes a body element and a head element having a thumb screw portion and a threaded portion. The body element includes a plurality of threaded finish structures. The body element may be configured to receive a collet along a longitudinal slot of the adjustable diameter step pin apparatus. The thumb screw portion may be configured to rotate to alter the collet and the threaded portion may be configured to engage with the plurality of threaded finish structures when assembled with the body element. In an embodiment, the head element may be rotatable to engage the threaded portion of the head element into the plurality of threaded finish structures to alter the collet while keeping the body element sturdy.

Abstract: A method includes receiving, using radio frequency (RF) collectors, RF signals from a target object. The RF signals of target object may be converted to In-phase and Quadrature (I/Q) data. Navigation data of each RF collector may be determined and I/Q data of each of RF collectors are paired. Processing functions may be applied on paired I/Q data. Using paired I/Q data, one or more of time difference of arrival (TDOA) measurement data and frequency difference of arrival (FDOA) measurement data between each pair of the RF collectors are determined. One or more of TDOA measurement data, FDOA measurement data and navigation data of each RF collector are converted to message data. A trajectory of target object may be estimated based on confidence measure of one or more of TDOA and FDOA measurement data. Using estimated trajectory of target object for displaying on a display device of a computing device.

Abstract: Technology is disclosed for an asset-based system for command and control of physical and cellular network assets onboard satellites. In an implementation, a computing device ingests indications of physical assets and cellular network assets deployed on satellites into a common format for entry into a satellite asset dataset. The computing device provides a user interface indicating representations of the satellites with corresponding representations of the physical assets and representations of the cellular network assets based on the ingested contents of the satellite asset dataset. The computing device receives orchestration control inputs relating to control or deployment of selected assets to initiate or alter a cellular network arrangement across the satellites in the user interface.

Abstract: Embodiments provide a universal bushing system that includes a base plate, vertical plates, and universal vector bushing apparatuses. The vertical plates are mounted to base plate and are separated by predetermined distance on base plate to position a workpiece. The bushing apparatuses are coupled to vertical plates. Each apparatus includes first knob, second knob, bushing element, and pivoting portion. The first knob includes threaded structures. The second knob is coupled to first knob via the threaded structures. The bushing element includes a recess with threaded tracks to allow the second knob to be placed. The pivoting portion includes a first end coupled to bushing element and a second end to pivotally connect to a vertical plate. Each of the first knob, the second knob, the bushing element, and the pivoting portion forms a hollow portion concentric at longitudinal axis that forms a slotted path to receive a threaded shaft.

Abstract: Systems and methods for an overheating control system for an electrical power harness disposed within an enclosure of an aircraft. The system includes a temperature sensor disposed within the enclosure and communicatively coupled to an electronic processor. The electronic processor is configured to monitor, via the temperature sensor, a temperature within the enclosure, compare the temperature to a predetermined threshold, and adjust a power output provided to one or more supply lines of the harness based on an amount in which the temperature exceeds the predetermined threshold.

Abstract: Provided herein are various enhancements for feed networks and aperture assemblies in radio frequency transmit/receive systems. In one example an apparatus includes a horn aperture integrated with a multimode feed network that can be monolithically fabricated in a single piece. The multimode feed network comprises a first feed section coupled between a first feed port and a first polarizer port of a polarizer and comprising a first waveguide filter and first waveguide stubs establishing first transmission zeros. The multimode feed network also includes a second feed section coupled between a second feed port and a second polarizer port of the polarizer and comprising a second waveguide filter and second waveguide stubs establishing second transmission zeros. The polarizer comprises a stepped septum positioned between the first polarizer port and the second polarizer port and having a shared port coupled to the horn aperture.

Abstract: Provided herein are various enhancements for solar panels and photovoltaic array assemblies. In one example, a system includes solar panel assemblies each comprising a frame defining a mounting area formed from modular segments having receiving features configured to accept spline elements that mount a perimeter of a flexible photovoltaic panel into the mounting area and apply a radial tension to the flexible photovoltaic panel. A stowage mechanism is configured to hold the solar panel assemblies in a stacked configuration and comprising a rod assembly disposed through apertures in the frames of each of the solar panel assemblies. A deployment mechanism is configured to deploy the solar panel assemblies from the stacked configuration into a deployed configuration and comprising self-opening hinges attached between selected pairs of the frames.

Abstract: A rotor assembly for a rotary wing aircraft includes a rotor hub, a rotor blade coupling coupled to the rotor hub, a hub extender coupled to the rotor hub, and a first bearing assembly. The first bearing assembly includes a clevis coupled to the hub extender and including two arms, each arm including a clevis opening, two cylindrical bearings, each cylindrical bearing extending through one of the clevis openings, a spherical bearing positioned between the two arms and coupled to the rotor blade coupling, and a first pin extending through the two cylindrical bearings and the spherical bearing.

Abstract: Systems and methods are disclosed for using a pressure relief shipping adapter to reduce the internal pressure of a container. A pressure relief shipping adapter includes a body comprising a first portion, a transitional portion, and a second portion. The first portion comprises a set of protrusions and a hole disposed through the set of protrusions. The second portion comprises an outlet disposed at a second end of the body. The outlet is concentric with an inlet disposed at the first end of the body. The transitional section is disposed between the first portion and the second portion. The pressure relief shipping adapter also includes an internal chamber within the body.

Abstract: According to some embodiments, a system includes a wireless test module (WTM) side hot-swap connector located between a chassis of a first WTM and a variable front end of the first WTM. The variable front end of the first WTM may mate to an aircraft connector. The WTM side hot-swap connector may mate to a front end side hot-swap connector of the variable front end of the first WTM. The WTM side hot-swap connector includes a female connector, an alignment peg configured to couple to the variable front end of the first WTM, a slip ring configured to secure the first WTM in place, and an electrically erasable programmable read-only memory (EEPROM) read/write wire integrated on a circuit board operable to read/write data of the aircraft connector.

Abstract: A method of curing a hollow thermoset composite (HTSC) structure is disclosed herein. In some embodiments, the method includes debulking a hollow thermoset composite (HTSC) structure in a female tool to have a first target bulk factor and a first target degree of cure (DOC), and curing the debulked HTSC structure. In some embodiments, curing the debulked HTSC structure further includes: (a) curing the debulked HTSC structure to have a second target bulk factor, a second target DOC and a target viscosity, wherein the second target bulk factor and the second target DOC are greater than the first target bulk factor and first target DOC, respectively; and (b) curing the HTSC structure resulting from step (a) to have a final target DOC, wherein the final target DOC is greater than the second target DOC.

Abstract: Methods of co-curing a sandwich structure are disclosed. In some embodiments, methods includes providing a sandwich structure comprising, in order, a first facesheet component; a first adhesive component; a core component; a second adhesive component; and a second facesheet component; curing the first and second facesheet components to a first facesheet degree of cure (DOC) and curing the first and second adhesive components to a first adhesive DOC, wherein the first facesheet DOC and the first adhesive DOC being a partially cured states, and wherein the first facesheet DOC is unequal to the first adhesive DOC; and curing the partially cured first and second facesheet components to a second facesheet DOC and curing the partially cured first and second adhesive components to a second adhesive DOC, wherein the second facesheet DOC being greater than the first facesheet DOC and the second adhesive DOC being greater than the first adhesive DOC.

Abstract: Provided herein are various enhancements for radio frequency feed structures for waveguide-fed antenna systems. A waveguide structure includes an outer waveguide cavity comprising radial ports and an outer aperture, and disposed coaxially about a piston polarizer element housing an inner waveguide cavity. The piston polarizer element comprises longitudinal ridges. The inner waveguide cavity comprises an axial port and an inner aperture disposed coaxially with the outer aperture.

Abstract: A system includes a laser drive assembly and a computer system. The laser drive assembly includes a laser that emits a laser beam to clean an end of a tube, a first motor that changes an angle of the laser beam with respect to the end of the tube, a second motor that moves the laser laterally, and a third motor that rotates the laser drive assembly around the end of the tube. The computer system is configured to clean the end of the tube by operating the laser to emit the laser beam, adjusting the angle of the laser beam with respect to the end of the tube by operating the first motor, adjusting the distance between the laser and the end of the tube by operating the second motor, and rotating the laser drive assembly around the end of the tube by operating the third motor.

Abstract: An assembly for controlling the orientation of a counterrotating rotor includes a main connecting member having a first and second end. A first connecting member, with a coupling end and an outer end, is rotatably coupled to the first end of the main connecting member via a hinge defining a first rotational axis. Similarly, a second connecting member, with a coupling end and an outer end, is rotatably coupled to the second end of the main connecting member via a hinge defining a second rotational axis parallel to the first. The assembly features a first rotor with blades and a motor mounted on the first outer end, and a second rotor with blades and a motor mounted on the second outer end. An actuator assembly applies torque to the connecting members, enabling rotation about their respective rotational axes, allowing precise control of the rotors' orientation for various applications.

Abstract: Provided herein are various enhancements for including selectable delay or phase shift lines in microwave radio frequency (RF) systems. One example includes RF switches coupled between an RF input and an RF output. A first tier of the RF switches is coupled through first RF delay lines that produce first selectable delays or phase shifts, and a second tier of the RF switches is coupled through second RF delay or phase shift lines that produce second selectable delays or phase shifts. Tier coupling RF switches couple the first tier and the second tier and establish a cascaded arrangement among outputs of the first tier and inputs of the second tier.

Abstract: A gearbox assembly includes a main housing, a plurality of gears, and a lubricant sump. The main housing defines an internal cavity. The gears are disposed within the internal cavity. The lubricant sump is coupled to the main housing. The lubricant sump includes a sump body and a heat exchanger core. The sump body defines a sump cavity and an airflow passage. The sump cavity is fluidly coupled to the internal cavity to collect lubricant used with the gears. The heat exchanger core is coupled to and extends from the sump body and is disposed at least partially within the airflow passage to cool the lubricant passing through the heat exchanger core.

Abstract: A sleeve removal tool for removing a split sleeve embedded in a structure includes a main rod, a nose cap, a housing, and a nut. The main rod includes a main threaded portion and a neck portion. The nose cap is configured to removably couple to the neck portion of the main rod and to removably couple to a flare of the split sleeve embedded in the structure. The housing includes a non-marking foot. The housing is configured to at least partially surround the main rod. The nut is configured to be threaded onto the main threaded portion of the main rod, wherein threading the nut onto the main threaded portion of the main rod forces the housing against the structure and forces the main rod away from the structure, thereby removing the split sleeve from the structure.

Abstract: A temporary fastener actuation tool includes a protrusion, multiple spring clips, and a bearing shaft. The protrusion includes a groove that matches a shape of an indentation of a temporary fastener. Each spring clip includes an end that is aligned with an end of the protrusion. The spring clips are configured to hold the indentation of the temporary fastener secure against the protrusion. The temporary fastener actuation tool further includes a first bearing that is coupled to the bearing shaft and is configured to contact a cylindrical body of the temporary fastener and rotate the cylindrical body of the temporary fastener in a first direction. The temporary fastener actuation tool further includes a second bearing coupled to the bearing shaft that is configured to contact a stem of the temporary fastener and to rotate the stem in a second direction. A motor shaft is coupled to the bearing shaft.