Abstract: A method of cleaning a recoater of an additive manufacturing machine includes installing a cleaning fixture into the additive manufacturing machine, the cleaning fixture including one or more cleaning elements, advancing the recoater into contact with the one or more cleaning elements, and rotating the recoater about a recoater axis thus dislodging material from a recoater outer surface due to frictional contact with the one or more cleaning elements.

Abstract: An additive manufactured workpiece includes one or more cavities having an inner surface. A dielectric interface is formed in the cavity, and conforms to the inner surface. The additive manufactured workpiece further includes an in-situ electrode in the cavities. The dielectric interface is interposed between the in-situ electrode and the inner surface of the workpiece.

Abstract: Selector lever systems of aircraft are provided. The selector lever systems include a selector lever configured to control operation of one or more aircraft control surfaces, the selector lever having a handle configured to enable manual operation of the selector lever, a touch sensor arranged on the handle, and a controller arranged in communication with the touch sensor, the controller configured to at least one of generate a notification when a signal is received from the touch sensor and unlock the selector lever from a locked state.

Abstract: Provided are embodiments for a circuit including a DC-DC converter for current controlled solenoid drive, the circuit includes a constant current source; a charge pump circuit comprising a plurality of stages. Each stage includes a capacitor configured to be charged to a predetermined voltage; a current source operable to charge the capacitor; a switch; and a controller that is configured to control switching of the switch for each of the plurality of stages based at least in part on an output current of the charge pump. Also, provided are embodiments of a method for operating a DC-DC converter for current controlled solenoid drive.

Abstract: A valve system includes a heat exchanger disposed within a heat exchanger manifold. The heat exchanger manifold has a first face defining a first flow inlet and an exhaust outlet, a second face disposed opposite the first face and defining a second flow inlet, a third face extending between the first face and the second face, and a first side and a second side disposed opposite the first side. The first side and the second side each extend between the first face, the second face, and the third face. A first torque motor assembly is mounted to the first side. A second torque motor assembly is mounted to the second side.

Abstract: A plate for use in a heat exchanger is includes: a first surface; a second surface; first, second and third discrete flow passages passing through the plate from the first surface to the second surface, the second flow passage extending around the first flow passage and the third flow passage extending around the second flow passage. A plurality of fins extend parallel to the first surface across the third flow passage and have a first surface extending parallel to the first surface of the plate and a second surface extending parallel to and spaced from the first surface of the fin; and one or more pins protruding from the first surface of at least some of the fins. The pins extend away from the second surface of the fins.

Abstract: Disclosed is a separation system including: a chamber comprising: an inlet for receiving a two-phase fluid; a first outlet for draining liquid contained in the two-phase fluid; a second outlet for egress of gas contained in the two-phase fluid; a cylindrical body disposed in the chamber having a plurality of channels through which, during use, the two-phase fluid travels from the inlet to the second outlet, and wherein the liquid within the two-phase fluid coalesces on the walls of the plurality of channels as the two-phase fluid passes through the plurality of channels and the liquid drains through the first outlet.

Abstract: A multiphase switched flux electric machine including a rotary drive shaft, a ferromagnetic salient pole rotor assembly operably coupled to the rotary drive shaft having a plurality of rotor teeth defining a circumferential outer periphery of the rotor assembly, and a stator assembly. The stator assembly includes a ferromagnetic stator core, a plurality of permanent magnets positioned substantially equidistant about an inner circumference of the stator core, a plurality ferromagnetic stator teeth mounted to the permanent magnets on the stator core with distal ends forming an inner periphery of the stator assembly, the inner periphery proximate the outer axial periphery of the rotor assembly separated by an air gap; and a plurality of stator coils with an axial active portions disposed within selected teeth of the plurality of ferromagnetic stator teeth.

Abstract: A torsion bridge for use in a servovalve includes a body extending along and adapted to rotate about a first axis; a passage extending through the body along a second axis substantially perpendicular to the first axis, the passage defining a first cylindrical surface having a radius R1; an annular groove formed in the first cylindrical surface. The annular groove includes: a second cylindrical surface extending substantially in the direction of the second axis, the second cylindrical surface having first and second ends and a radius R2, where R2 is greater than R1; a first annular surface joining the first cylindrical surface to the first end of the second cylindrical surface; and a second annular surface joining the second end of the second cylindrical surface to the first cylindrical surface.

Abstract: A stop pin for a check valve includes a first end and a second end and extending from the first end to the second end in a longitudinal direction along a longitudinal axis. The stop pin also includes at least one slot therein extending in said longitudinal direction, said at least one slot defining a respective at least one flexible, cantilevered tongue having a free end and a connected end connected to said stop pin.

Abstract: Disclosed is an energy management system for an aircraft. The system includes an electric machine including a stator surrounding a rotor having permanent magnets disposed therein, wherein rotation of the rotor causes an alternating current to be generated in windings of the stator that is uncontrolled. The system includes an electric propulsion system. The system includes a bidirectional power converter having a first side connected to the electric machine and a second side galvanically isolated from the first side and connected to the electric propulsion system. The bidirectional power converter includes a switching network that regulates power associated with the electric machine and power transfer across the bidirectional power converter. The switching network is operable to satisfy collective power flows of the electric machine and the electric propulsion system through the bidirectional power converter.

Abstract: A system is provided. The system includes a first inlet providing a medium from a source, a compressing device in communication with the first inlet, and at least one heat exchanger. The compressing device includes a compressor that receives the medium, a first turbine downstream of the compressor, and a second turbine that receives the medium. An outlet of the at least one heat exchanger is in fluid communication with an inlet of the compressor and an inlet of the first turbine.

Abstract: Fuel tank inerting systems for aircraft are provided. The systems include a fuel tank, a catalytic reactor arranged to receive a first reactant from a first reactant source and a second reactant from a second reactant source to generate an inert gas that is supplied to the fuel tank to fill an ullage space of the fuel tank, a heat exchanger arranged between the catalytic reactor and the fuel tank and configured to at least one of cool and condense an output from the catalytic reactor to separate out the inert gas, and a controller configured to perform a light-off operation of the catalytic reactor by controlling at least one light-off parameter and, after light-off occurs, adjusting the at least one light-off parameter to an operating level, wherein the at least one light-off parameter comprises a space velocity through the catalytic reactor.

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, at least one dehumidification system arranged in fluid communication with the ram air circuit, a compressing device arranged in fluid communication with the ram air circuit and the dehumidification system, and an expansion device arranged in fluid communication with the ram air circuit and the at least one dehumidification system.

Abstract: A method is disclosed for treating an anodized metal surface. According to the method, polynuclear clusters comprising aluminum oxide hydroxide are applied to the anodized metal surface.

Abstract: A CAN network synchronization method identifies a sync master node from a plurality of nodes, and designates each of the remaining nodes as a sync slave node. The method further designates a message from the sync master node as a sync message, and assigns a lowest number to the message ID of the sync message. The method further assigns a unique node ID to each sync slave node, and assigns a unique message ID to a transmission duration report message from a sync slave node. The method further assigns a unique message ID to a transmission target time allocation message from the sync master node. The method also performs a handshake operation between the sync slave nodes and the sync master node to exchange message burst transmission durations (Tsst), transmission target times (TTXtarget), and a common time reference point, and conducts time adjustment on each sync slave node.

Abstract: A system includes an air turbine starter having an inlet, a turbine air exhaust outlet, an output shaft, and a turbine in fluid communication with the inlet and the turbine air exhaust outlet. The turbine is operably coupled to the output shaft. The system also includes an outlet valve assembly configured to adjust an exhaust area of the turbine air exhaust outlet.

Abstract: An intermediate thrust plate is provided to absorb thrust loads while permitting rotation and deflection of a butterfly valve shaft. The intermediate thrust plate includes a body having upper and lower surfaces and defining an aperture extending through the body between the upper and lower surfaces, the upper surface extending annularly about the aperture and being substantially flat, the lower surface extending annularly about the aperture and having a spherical shape and at least the lower surface including a low-friction material.

Abstract: An inverted harmonic gear actuator is provided and includes a motor stator and a motor rotor radially disposed within the motor stator. The inverted harmonic gear actuator also includes a wave generator radially disposed within the motor rotor, where the wave generator has a radially inner surface with a cammed shape. An actuator output shaft is radially disposed within the wave generator. A flex spline is radially interposable between the radially inner surface of the wave generator and the actuator output shaft. The flex spline is deformable to conform to the radially inner surface of the wave generator and drive rotation of the actuator output shaft slower than rotation of the motor rotor.

Abstract: A fault detection circuit includes a system controller and a fault detection controller. The system controller includes at least one memory device to control at least one electrical system. The fault detection controller communicates with the system controller to detect at least one fault of the system controller and to control operation of the system controller based on comparison between a frequency of detected faults corresponding to the system controller and at least one frequency threshold value.