Abstract: An article includes a body, which includes a thermoplastic or thermoset material and a plurality of metallic fibers distributed throughout the thermoplastic or thermoset material and has a first subset of the plurality of metallic fibers extending onto a first surface of the body. The manufactured article includes a metallic coating metallically bonded to the first subset of the plurality of metallic fibers. The metal fibers extending onto the first surface are configured to bond with the metallic coating.

Abstract: A system of an aircraft includes an inlet arranged in fluid communication with a bleed air source such that the inlet is configured to receive a flow of bleed air. A compressing device includes a compressor having a compressor inlet fluidly connected to the inlet. A heat exchanger is fluidly coupled to an outlet of the compressor. The heat exchanger includes a first pass and a second pass, both of which are located downstream from the compressor. An outlet of the first pass is directly connected to an inlet of the second pass via a first conduit. The outlet of the first pass is also fluidly connected to an inlet of the compressor via a second conduit such that a portion of the bleed air output from the first pass is returned to the compressor inlet via the second conduit.

Abstract: A heat exchanger manifold configured to receive or discharge a first fluid includes a primary fluid channel and a plurality of secondary fluid channels. The primary fluid channel includes a fluid port and a first branched region distal to the fluid port. The plurality of secondary fluid channels are fluidly connected to the primary fluid channel at the first branched region. Each of the plurality of secondary fluid channels includes a first end and a second end opposite the first end. Each of the plurality of secondary fluid channels extends radially from the first branched region at the first end and has an equal length from a center of the first branched region to the second end.

Abstract: A packed bed for a heat exchanger may comprise a frame and a first fin layer disposed within the frame. A second fin layer may be disposed within the frame. A first perforated sheet may be disposed between the first fin layer and the second fin layer. A sorbent material may be disposed within a volume of at least one of the first fin layer or the second fin layer.

Abstract: A method of manufacturing a component includes making a preform from a powdered material, the preform having a density in a range from 70 to 95% of theoretical density of the material, The method also includes sintering the preform using a Field Assisted Sintering Technique (FAST) process to produce a component having a density of greater than 97% of the theoretical density of the material. Components, in particular low aspect components, formed by said method are also described.

Abstract: A blade for a propeller including a blade composite structure includes a Fiber Bragg Grating (FBG) or an Extrinsic Fabry-Perot Interferometric (EFPI) sensor embedded in the blade composite structure. The sensor is configured to receive a signal from a controller operatively connected to the FBG or EFPI sensor, and transmit a signal, responsive to the received signal, to a processor operatively connected to the sensor. The signal response is indicative of a stress measurement indicating a structural characteristic of the blade composite structure. The signal response provides information to determine, based on the signal response, whether the structural characteristic of the blade composite structure is within a predetermined limit indicative of structural integrity of the blade composite structure.

Abstract: An inverted compound harmonic drive including: a wave generator configured to receive rotational input; a flex spline disposed radially within the wave generator that receives energy due to the rotation of the wave generator, the flex spline including a plurality of inner facing splines that include an axial center spline, a first axial end spline being adjacent to and forward of the axial center spline, and a second axial end spline adjacent to and aft of the axial center spline; an output gear meshes with the axial center spline; a first ground gear adjacent to and forward of the output gear that meshes with the first axial end spline; and a second ground gear adjacent to an aft of the output gear that meshes with the second axial end spline.

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having a heat exchanger positioned therein and a dehumidification system arranged in fluid communication with the ram air circuit. A plurality of expansion devices is arranged in fluid communication with the ram air circuit and the dehumidification system. At least one of the expansion devices is a simple cycle expansion device.

Abstract: A fuel delivery system includes a turbine, a pump, and an oxygen removal unit. The turbine is adapted to receive and expel fuel at different pressures. The pump is in fluid communication with, and mechanically coupled to, the turbine, and is configured to expel and receive the fuel at about the respective different pressures. The turbine is configured to convert pressure energy of the fuel to kinetic energy to drive the pump. The oxygen removal unit is in fluid communication with at least one of the turbine and the pump, and is configured to remove oxygen from the fuel.

Abstract: A hydraulic piston actuator, which may be used for an aircraft nacelle assembly, includes a housing, a piston, an end gland, and a bearing ring. The housing is concentrically disposed along an axis. The piston is adapted to axially reciprocate within the housing. The end gland is disposed radially between the housing and the piston. The bearing ring is disposed radially between the end gland and the piston.

Abstract: A servo valve comprises a valve housing, a cavity formed in the valve housing and defining a longitudinal axis (X), and a member disposed in the cavity and axially-moveable therein, wherein the member comprises a portion with first and second cylindrical sections having a first diameter (R1, R2), a central section located between the first and second cylindrical sections and having a second diameter (R3), and first and second frusto-conical sections connecting the first and second sections to the central section and forming respective first and second frusto-conical surfaces. A plurality of ports, each form a fluid passage through the valve housing and have first and second nozzles with first and second nozzle openings.

Abstract: Provided are embodiments for a system including an adaptive controller, wherein the system includes a hydraulic actuator including a fluid medium, and a sensor that is disposed on the hydraulic actuator, wherein the sensor is configured to obtain sensor data of the actuator. The system also includes a processor configured to calculate an ultrasonic velocity in the fluid medium using the sensor data, wherein the processor is further configured to determine a temperature of the fluid medium based at least in part on the calculated velocity, and a controller coupled to the actuator, wherein the controller is configured to control the actuator based at least in part on the calculated velocity and determined temperature. Also provided are embodiments for a method for operating the adaptive controller.

Abstract: An embodiment of a linear motor assembly includes an armature extending linearly along an axis, the armature having a plurality of windings. The linear motor assembly also includes a magnetic assembly including a plurality of magnets arrayed in a loop configuration, a linear section of the plurality of magnets extending linearly through the plurality of windings in a direction parallel to the axis, each magnet of the linear section being oriented in the direction and configured to move in the direction due to interaction between the plurality of windings and a magnetic field generated by the magnetic assembly.

Abstract: A pin and carrier locking assembly is described for locking a pin and carrier in position relative to each other. The carrier has first and second opposing arms, each comprising a bore therein and the axial ends of the pin are positioned within these opposing bores of the carrier. The assembly further comprises a hollow bearing provided around and coaxially with said pin and between said first and second arms. The bearing is positioned so as to not contact the first arm of the carrier but to contact the second arm of the carrier and a washer is positioned between the bearing and the first arm of the carrier so that a first section of the washer makes a first contact area with the first arm of the carrier.

Abstract: A servo valve includes a valve housing, a cavity formed in the valve housing defining an axis (X) and an axially moveable member disposed in the cavity. The member comprises flat surfaces parallel to the axis (X). A channel is formed within the cavity and a plurality of ports each forming a fluid passage through the valve housing in fluid communication with a spool and with the channel. The plurality of ports include first and second nozzles with nozzle openings, wherein in a first axial position of the member the first nozzle opening is at least substantially obstructed by the first flat surface, and in a second axial position of the member the second nozzle opening is at least substantially obstructed by the second surface, the member controlling fluid between the spool and the channel.

Abstract: An integrated turbo-compressor includes a compressor with a compressor outlet, a turbine with a turbine inlet, the turbine operatively connected to the compressor by an interconnect shaft, and a compounding drive. The compounding drive is connected to the turbine and has a variable gear ratio and an output member, the variable gear ratio coupling the turbine to the output member to compound output of an internal combustion engine using energy recovered from an exhaust flow received from the internal combustion engine and in excess of energy required to compress combustion air provided to the internal combustion engine. Internal combustion engines, aircraft, and methods of compounding output of internal combustion engines are also described.

Abstract: A servovalve includes: a fluid transfer valve assembly comprising a supply port and a control port; a moveable valve spool arranged to regulate flow of fluid from the supply port to the control port in response to a control signal; and a jet pipe assembly configured to axially move the valve spool relative to the fluid transfer assembly in response to the control signal to regulate the fluid flow. The spool includes a tubular body defining a path for fluid flow, the tubular body closed at each end by a respective end cap having openings via which, in use, fluid enters the interior of the spool. The end caps extend within the tubular body at least to an extent that they overlap the openings, and wherein the end caps are provided with filter means for filtering the fluid from the openings as it enters the spool.

Abstract: An additive manufacturing product is provided. The additive manufacturing product includes an embedded electronic, a transition zone, and a base material. The transition zone encases the embedded electronic. The transition zone includes transition material. The base material encases the transition zone. The transition material includes an intermediate melting point that is lower than a melting point of the base material.

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein, a dehumidification system arranged in fluid communication with the ram air circuit, and a compressing device arranged in fluid communication with the ram air circuit and the dehumidification system. The compression device includes a compressor and a first turbine coupled to one another via a shaft. During operation of the first turbine, work is extracted from a first medium within the first turbine to power the compressor. At an outlet of the first turbine, a temperature of the first medium is above freezing and at least a portion of the moisture within the first medium is condensed.

Abstract: The present disclosure relates to an apparatus for a torque limiter, comprising an indication device configured to provide an indication that the torque limiting device has tripped, and of the direction of torque applied to the torque limiting device when the torque limiting device tripped, in use.