Abstract: A method for verifying and authenticating additive manufactured products utilizing extraterrestrial communication including generating a product geometry file, recording to a distributed transaction register stored on a server network having a plurality of node servers a first transaction reflecting the product geometry file, the first transaction having a first output associated with the first transaction and including a blockchain address, transmitting the first output between a terrestrial transceiver that is communicatively connected to the server network and an extraterrestrial transceiver that is communicatively connected to the terrestrial transceiver, and printing, with a 3D additive printer, a product that utilizes the product geometry file.

Abstract: A method for the verification and authentication of additive manufactured product, comprising the steps of receiving, from a customer, at least one customer requirement for a product, deriving at least one manufacturing requirement and generating a product geometry file for the product, recording, by a first computing device, to a distributed transaction register, a first transaction reflecting certification of the product geometry file, obtaining a first output reflecting the first transaction, printing the product with a 3D printer, recording, by a second computing device, to the distributed transaction register, a second transaction reflecting the printing of the product and the first output, obtaining a second output reflecting the second transaction, embedding within the product a unique code reflecting the second output, whereby the product geometry file and the printing of said product may be verified with the unique code such that the product may be authenticated.

Abstract: A variable reluctance resolver with a stator assembly including a printed circuit board having a first surface and a second surface. A plurality of inductors coupled with the annular printed circuit board first surface, wherein the plurality of inductors are in electrical connection with a power source. The variable reluctance resolver also having a rotor including a body with a first surface and a second surface, an annular recess located in the rotor first surface. The annular recess including a radially inner surface and a radially outer surface, wherein the annular recess defines a width variable with angular position. The plurality of inductors are located at least partially within the annular recess and the rotor is operable to rotate relative to the stator assembly.

Abstract: An electric motor assembly comprising a housing containing a secondary power source, a motor driver, an electric motor, power sensors to sense faults in a primary power supply and the secondary power source, primary and secondary winding sensors configured to sense faults in a primary winding and a secondary winding of the electric motor, the motor driver comprising a primary controller to control the primary winding in a normal operation mode and a secondary motor controller operatively configured to control at least one of the primary winding and/or the secondary winding in a secondary operation mode, the secondary motor controller configured to drive the motor to a safe position using the secondary winding in the event of a sensed fault in the primary winding and to drive the motor to the safe position using the secondary power source in the event of a sensed fault in the primary power source.

Abstract: A failsafe vale provides “Hole-In-The-Wall” failsafe functionality for thin-wing aircraft control surface actuation systems having a geared rotary actuator powered by a hydraulic rotary motor. The failsafe valve is associated with the hydraulic rotary motor and mechanically connected to the control surface, and enables the flight control surface to return to an aerodynamically neutral failsafe position if electrical control and/or hydraulic pressure is lost. When the failsafe valve receives a normal command pressure from the hydraulic system, the valve is inactive and the actuation system operates normally. However, if there is a loss of electrical command capacity to control hydraulic valves and/or a loss of hydraulic pressure, the failsafe valve is activated and connects one of the motor hydraulic control lines to the case return line for the motor if the control surface is away from its failsafe position.

Abstract: A three-dimensional monolithic diaphragm tank including a first portion having a first inner surface, a second portion having a second inner surface, and a deformable diaphragm extending from a peripheral junction with the first inner surface and the second inner surface. The first inner surface and the diaphragm defining a first chamber. The second inner surface and the diaphragm defining a second chamber. The first portion having an outlet port in fluid communication with the first chamber, and the second portion having an inlet port in fluid communication with the second chamber. The peripheral junction of the diaphragm and the first inner surface including an integral inner fillet having an inner radius.

Abstract: A rotor blade pitch control system (15) comprising a rotor blade (19a, 19b, 19c, 19d) rotatable about both a central axis (20) and a pitch axis (24a, 24b, 24c, 24d), a pitch drive rotor (32a, 32b, 32c, 32d) rotatable about the central axis independently of rotation of the rotor blade about the central axis, a pitch follower (40a, 40b, 40c, 40d) rotatable relative to the pitch drive rotor, the pitch drive rotor and the pitch follower having an eccentric axis (33a, 33b, 33c, 33d), a linkage (50a, 50b, 50c, 50d) between the pitch follower and the rotor blade configured such that the pitch follower rotates with rotation of the rotor blade about the central axis, the pitch drive rotor, the pitch follower and the linkage configured such that the pitch drive rotor may be driven to control an angular displacement of the pitch drive rotor relative to the pitch follower about the central axis and thereby control the pitch of the rotor blade about the pitch axis.

Abstract: A rotary actuator has a stop module configured to mechanically link two gear stages travelling at different rotational speeds when an end-of-stroke travel limit is reached, thereby causing the rotary actuator to bind because relative motion between the gear stages is impeded.

Abstract: A battery cell cooling assembly for a vehicle comprising a cooling vessel having a coolant flow path between an inlet and outlet, cell apertures exterior to the flow path, a first directional directing coolant from the inlet into laterally spaced first sub-channels, a second directional receiving coolant from the first sub-channels and directing it into laterally spaced second sub-channels, the first sub-channels extending transversely between the cell apertures and aligned longitudinally between first aperture ends and second aperture ends of the cell apertures, the second sub-channels extending transversely between the cell apertures and aligned longitudinally between the first sub-channels and the second aperture ends, wherein the first sub-channels provide a first thermal pass by each of the plurality of cell apertures and the second sub-channels provide a second thermal pass by each of the same plurality of cell apertures for temperature control of the cells during operation.

Abstract: A stop module for non-jamming end-of-stroke stoppage of a rotary drive actuator includes timing gears to articulate a stopping pawl, and a low inertia, deformable stopping disk arranged to safely dissipate excess rotational kinetic energy of the rotary actuator. The stop module does not rely on friction to stop and dissipate the excess kinetic energy, but instead relies on predictable deformation of a metallic stopping disk which may be provided in a stopping cartridge of the stop module. Use of a deformable element to dissipate excess energy allows the disclosed stop module to be lighter and smaller than conventional end-of-stroke stopping mechanisms.

Abstract: An actuator assembly comprising an output member rotatable about a center axis relative to a structure, a first actuator having a first stator fixed to the structure and a first rotor rotatable about the center axis relative to the first stator, a second actuator having a second stator coupled to the first rotor such that the second stator rotates about the center axis relative to the first stator with rotation of the first rotor about the center axis and having a second rotor rotationally coupled to the output member, a controller configured in a failure mode to drive one of the first actuator or the second actuator to selectively control the rotation of the output member about the center axis with an operational failure of the other of the first actuator or the second actuator.

Abstract: A mechanism for loading suspended loops of linked ammunition onto rails of an ammunition magazine includes a guideway and a carriage. The guideway has cam surfaces and cam slots each extending vertically from a lower portion of the guideway and curving near an upper portion of the guideway toward the rails at a loading end of the magazine. The carriage includes a support block slidably received by the guideway and a tandem bucket mounted on the support block by a linkage. The tandem bucket includes inner and outer followers engaging the cam surfaces and cam slots. The tandem bucket is horizontal and may be loaded with two adjacent rounds of a belt of linked ammunition when the carriage is at a lowered position. The carriage may then be raised manually, wherein the tandem bucket is articulated by camming engagement of the followers to a vertical orientation to deposit one of the two rounds onto the magazine rails with the other round and trailing rounds suspended therefrom.

Abstract: A probe for receiving transmissions of electrical signals from a transmitter across an interface of a slip ring comprising a signal capture area comprising at least one segmented signal receiving strip arranged in spaced relation to the transmitter of the slip ring for receiving a signal transmitted across the interface of the slip ring. The segmented signal receiving strip configured to receive a range of frequency signal content of the signal and having a first signal receiving segment having a first frequency response, a second signal receiving segment electrically coupled to said first signal receiving segment and having a second frequency response less than the first frequency response, and a third signal coupled to the first signal receiving segment and having a third frequency response less than the first frequency response.

Abstract: A claw-pole motor having a rotor assembly orientated about a longitudinal axis, a stator assembly having a first plurality of stator teeth and a second plurality of stator teeth orientated radially about the longitudinal axis and extending axially in opposite directions to each other and alternating about the longitudinal axis, a first gap in the stator assembly orientated about the longitudinal axis, a second gap orientated about the longitudinal axis and extending both axially and radially between the first plurality of stator teeth and the second plurality of stator teeth, first electromagnetic windings disposed in the first gap and second electromagnetic windings disposed in the second gap, the first and second windings configured to be selectively energized to exert a torque on the rotor assembly.

Abstract: Embodiments of the present disclosure provide a system, method, apparatus and computer-readable medium for teleoperation. An exemplary system includes a robot machine having a machine body, at least one sensor, at least one robot processor, and at least one user processor operable to maintain a user simulation model of the robot machine and the environment surrounding the robot machine, the at least one user processor being remote from the robot machine. The system further includes at least one user interface comprising a haptic user interface operable to receive user commands and to transmit the user commands to the user simulation model, a display operable to display a virtual representation of the user simulation model.

Abstract: A vibration suppression unit for an aircraft comprising a vibration control frame adapted to be mounted to the aircraft and to rotate about a central axis, a first motor configured to rotate the vibration control frame about the central axis, a second motor configured to rotate a first and second center of mass about a first and second axis or rotation, a third motor configured to adjust a variable distance between the first and second centers of mass and the first and second axis of rotation, respectively, and a controller for receiving input signals and outputting command signals to the first, second and third motors.

Abstract: A claw-pole motor comprising a non-magnetic rotary shaft having a longitudinal axis, a plurality of flux concentrators extending along the longitudinal axis of the rotary shaft, and a plurality of magnetic claw poles extending along the longitudinal axis of the rotary shaft, each of the plurality of flux concentrators alternating with each of the magnetic claw poles about the rotary shaft, and a stator having a plurality of coil assemblies, each coil assembly including a solenoid coil and an enclosure having a upper portion and lower portion, the upper portion and the lower portion of the enclosure having alternating stator teeth about the longitudinal axis.

Abstract: A vibration suppression unit for an aircraft comprising a mass having a center of mass, a first rotor, a second rotor, a first coupling between the first rotor and the mass, a second coupling between the second rotor and the mass, the first and second couplings having first and second coupling centers offset perpendicularly from a central axis of rotation by different radial distances and offset in axially from the center of mass with respect to the central axis by different axial distances, the first and second coupling centers having a selectively variable displacement angle defined by the angle between lines extending between the central axis of rotation and the first coupling center and the second coupling center, respectively, wherein the first rotor and the second rotor are controllable to produce a vibration control force vector having a controllable magnitude and frequency about the central axis.

Abstract: A rotor assembly of an electric motor generally comprises a center shaft configured to rotate about a longitudinal axis and a plurality of spacers extending radially outward from the center shaft, the spacers fixedly attached to the center shaft. A plurality of axially stacked annular laminations are coaxially aligned with the center shaft and radially supported on an inner circumferential surface by the plurality of spacers. Each of the plurality of spacers has, at each axial end of the stacked annular laminations, first and second axial restraining elements extending in an outward radial direction beyond the inner circumferential surface of the plurality of stacked annular laminations. The plurality of stacked annular laminations are compressed between the first axial restraining element and the second axial restraining element, such that an axial compression force is applied to the plurality of stacked laminations.

Abstract: A vibration suppression unit for an aircraft comprising a mass assembly having a center of mass and a frequency rotor having a frequency center axis offset from a central axis of rotation and driven to rotate about the central axis, a vibration control amplitude rotor rotationally coupled to the mass assembly and having an amplitude center axis offset from the central axis driven independently of the frequency rotor to rotate about the central axis, the amplitude center axis and the frequency center axis having a selectively variable displacement angle defined by an inclusive angle between a line extending between the central axis and the amplitude center axis and a line extending between the central axis and the frequency center axis, wherein the amplitude rotor and the frequency rotor are controllable to produce a vibration control force vector having a controllable magnitude and frequency about the central axis of rotation.