Abstract: An aircraft actuation system is disclosed that includes a pair of cylinders, a piston movably disposed in each cylinder, and a roller train that extends between the pistons in the two cylinders. A portion of the roller train is disposed beyond the cylinders to engage a pinion. Movement of the pistons in the two cylinders in opposite directions produces a corresponding movement of the roller train to in turn rotate the pinion. The roller train may be maintained in compression between its two ends by fluid pressure exerted on a common face of each of the pistons in the two cylinders. The cylinders may be disposed in non-colinear relation, including in parallel relation to one another. A guide may be used to maintain rollers of the roller train in a proper orientation for entry into a space between an outer race and the pinion.

Abstract: A steering apparatus may comprise a steering collar, a first linear actuator, a first drive gear, a crankshaft, and a sun gear, wherein the sun gear is disposed within the collar, wherein the first drive gear is fixed to the crankshaft and coupled to the sun gear such that the collar rotates about the sun gear in response to rotation of the crankshaft, wherein the first linear actuator is coupled between the crankshaft and the collar.

Abstract: A cargo handling system may utilize a leaky feeder antenna grid to determine the location of a ULD, a mobile cargo controller, or both within a cargo compartment. This location determination may be used for any appropriate purpose. For instance, the noted location determinations may be used to alert an operator of an approaching ULD, to terminate motion of an approaching ULD, or both.

Abstract: A cargo handling system that utilizes a distributed antenna system for a cargo bay or compartment is disclosed. A cargo deck within the cargo bay may incorporate a plurality of power drive units. A mobile cargo controller may wirelessly communicate with the distributed antenna system to control movement of a ULD into/out of/within the cargo bay. A base station may be operatively interconnected with both the distributed antenna system and the plurality of power drive units (e.g., directly or indirectly via a control system, such as a control panel).

Abstract: Methods, systems, and apparatuses for component manufacturing are provided. A component may be manufactured via an extrusion of loose substrate material into a unitary tubing. Features may be added to the tubing via friction stir additive manufacturing to manufacture a component. In this manner, a component may be manufactured from titanium alloys while processing challenges such as iron segregation or material loss through machining are ameliorated. Such a component may replace steel or other high strength components and further exhibits corrosion resistance.

Abstract: A frame for an opto-mechanical support structure includes an interconnected lattice of frame composite rods defined about an interior space with interstices defined between the frame composite rods. A method of making an opto-mechanical frame includes forming a frame of interconnected lattice of frame composite rods using one or more Automated Fiber Placement (AFP) around a mandrel. The method includes removing the mandrel from an interior space of the frame after forming the frame.

Abstract: A steering apparatus may comprise a strut cylinder, a steering collar, a first linear actuator, a first drive gear, a crankshaft, and a ring gear. The ring gear may be coupled to the steering collar. The first drive gear may be fixed to the crankshaft and coupled to the ring gear such that the steering collar rotates in response to rotation of the crank shaft. The first linear actuator may be coupled between the crankshaft and the strut cylinder.

Abstract: A drive wheel for a power drive unit of a cargo handling system is disclosed. One aspect of the drive wheel is that it includes one or more wear indicators for a tire of the drive wheel. Another aspect of the drive wheel is that it includes one or more features (e.g., at least one protrusion, alone or in combination with one or more slots) that resists relative rotational movement between the tire of the drive wheel and the hub of the drive wheel.

Abstract: A restraint arrangement for an inflatable slide may comprise a releasable restraint and a yoke coupled to the releasable restraint. The yoke may comprise a first strap and a second strap. A first dampener may be coupled to the first strap. A second dampener may be coupled to the second strap. The first dampener and the second dampener may deform in response to a tensile load.

Abstract: A dielectric insulating insert arranged to be positioned between a drive shaft and a ball shaft of a motorised ball valve assembly. The insert includes a body of dielectric material to form an insulating layer and having opposing sides from each of which extends an engagement portion having a non-circular cross-section and configured to engage, respectively, with the drive shaft and the ball shaft in torque transfer engagement.

Abstract: A double eccentric bushing arrangement comprises a first eccentric bushing comprising a first eccentric aperture, a second eccentric bushing comprising a second eccentric aperture, a fastener, a washer configured to be received around a portion of the second eccentric bushing, and a snap ring configured to be received around a portion of the second eccentric bushing to secure the washer in an installed position. The first eccentric bushing is configured to receive the second eccentric bushing in the first eccentric aperture. The second eccentric bushing is configured to receive the fastener in the second eccentric aperture. The first eccentric bushing is rotatable with respect to the second eccentric bushing to adjust a position of the fastener with respect to an adjacent component to which the fastener is being attached.

Abstract: An aircraft landing gear actuation system which uses two separate actuation forces to retract aircraft landing gear is disclosed. One of the actuation forces may be provided by an actuator, such as a hydraulic actuator. Another of these actuation forces may be provided by a pressurized fluid that is directed into the actuator through a conduit that extends into a hollow interior of an actuator rod of the actuator. The pressurized fluid may be provided from a pressurized fluid source that contains a fixed volume of pressurized fluid. This pressurized fluid may exert a force on an actuator piston of the actuator or the actuator rod. The pressurized fluid may also be used to dampen the deployment of the landing gear.

Abstract: Systems and methods for forming an oxidation protection system on a composite structure are provided. In various embodiments, the oxidation protection system comprises a boron-glass layer formed on the composite substrate and a silicon-glass layer formed over the boron-glass layer. Each of the boron-glass layer and the silicon-glass layer include a glass former and a glass modifier.

Abstract: A de-icing light assembly may comprise: a housing; a plurality of lights coupled to the housing; a lens assembly coupled to the housing, the lens assembly comprising: a lens material; an indium tin oxide (ITO) film disposed on the lens material; and a silicon oxide coating disposed on the ITO film.

Abstract: A method of manufacturing a high-pressure fluid vessel includes forming a first portion of a high-pressure fluid vessel with a molding process. The high-pressure fluid vessel includes a stack of capsules. Each capsule includes a first domed end, a second domed end, and a semicylindrical portion extending between and connecting the first domed end to the second domed end. The method further includes forming a second portion of a high-pressure fluid vessel with the molding process. The second portion of the high-pressure fluid vessel is positioned adjacent to the first portion of the high-pressure fluid vessel. The second portion of the high-pressure fluid vessel is welded to the first portion of the high-pressure fluid vessel.

Abstract: A method is provided for producing ultra-fine-grained materials using additive manufacturing. The method includes commanding, by a controller, a laser device to produce a plurality of optical pulses to a base material to add an additive material to the base material. The method further includes commanding, by the controller, a vibration mechanism to vibrate the base material as the plurality of optical pulses are being applied to the base material forming fine equiaxed grains with random crystallographic texture in the base material.

Abstract: A modular wheel assembly for a power drive unit (PDU) may comprise a hub and a disc stack coupled to the hub. The hub may be a splined hub defining a plurality of spline recesses. The disc stack may comprise a plurality of discs. Each disc of the plurality of discs may comprise a ring having a plurality of splines that are complementary to the spline recesses, and that are configured to interlock with the spline recesses. Each disc may further comprise an annular segment made of one of a first material and second material. The annular segment may be a tire. In the event of damage or wear, each disc in the plurality of discs may be removed and repaired or replaced.

Abstract: An additive manufacturing system and process for manufacturing aircraft parts is disclosed. The process applying an additive manufacturing process to a build tube formed around a longitudinal axial direction of the build tube by rotating the build tube around a longitudinal axis. Then, translating, by the additive manufacturing process, a print-head in a parallel configuration to the longitudinal axis to enable the print-head to deposit an aerospace grade material on a surface of the build tube to form a manufactured component. After completion of the additive manufacturing process, applying another process using a device wherein the device applies a machining process in the longitudinal axial direction to remove the build tube wherein the machining process comprising machining an interior surface of the manufactured component to expose the interior surface of the manufactured component.

Abstract: A braking system for an aircraft is disclosed herein. The braking system may comprise: a brake assembly; a hydraulic braking subsystem having a hydraulic brake actuator configured to operate the brake assembly; an electric braking subsystem and a hydraulic braking subsystem. During a flight, one of the electric braking subsystem and the hydraulic braking subsystem may be selected as a primary braking system. The braking system may be configured to command braking of a brake assembly by the hydraulic braking subsystem and the electric braking subsystem during an RTO phase of the flight. The braking system may be configured to command braking of a brake assembly by a secondary braking system in response to a failure of a primary braking system during the RTO phase of the flight.

Abstract: A braking system for an aircraft may comprise: a brake assembly; a hydraulic braking subsystem having a hydraulic brake actuator configured to operate the brake assembly; an electric braking subsystem having an electric brake actuator configured to operate the brake assembly and a load cell configured to measure a force supplied by the electric brake actuator; a hydraulic brake control unit configured to control the hydraulic braking subsystem; and an electric brake control unit configured to control the electric braking subsystem, the electric brake control unit in operable communication with the hydraulic brake control unit, the electric brake control unit configured to calibrate the load cell by a scale factor based on a measured force from the load cell, a measured hydraulic pressure used to exceed the measured force received from the hydraulic brake control unit, and a piston area of the hydraulic brake actuator.