Abstract: A linear actuator includes a thrust bearing that is integral to the actuation member. The actuator includes a translation member and an actuation member. The actuation member is responsive to a drive force to rotate. The translation member is configured to translate in response to actuation member. The thrust bearing is coupled to the actuation member and includes an inner race, an outer race, and a plurality of balls. The thrust bearing is configured as a zero lead ballscrew, with the inner race integrally formed on the actuation member, and the plurality of balls disposed between the inner and outer races.

Abstract: A no-back device for a power drive unit is configured such that, during operation of the power drive unit, the no-back device does not supply magnetic or frictional force against power drive unit rotation. The no-back device is implemented either redundantly or no-redundantly, and includes a latch rotor and an electromagnet. In both embodiments, the latch rotor is coupled to the power drive unit to rotate therewith, and the electromagnet is coupled to receive a flow of current and, upon receipt thereof, generates a magnetic field force that opposes rotation of the latch rotor. In the redundant embodiment, the no-back device further includes one or more permanent magnets, and the magnetic field generated by the electromagnet selectively opposes or aids the magnetic field supplied by the permanent magnet(s).

Abstract: An object ejection system uses an energy storage flywheel to drive the fluid pump that is used to pressurize the ejection tubes. The energy storage flywheel is periodically spun-up using an electric motor. The energy stored in the energy storage flywheel is used, when needed, to drive the fluid pump and supply pressurized fluid to an impulse tank. The pressurized fluid in the impulse tank is used to eject an object, such as a weapon, from one or more ejection tubes.

Abstract: A linear actuator includes a thrust bearing that is integral to the actuation member. The actuator includes a translation member and an actuation member. The actuation member is responsive to a drive force to rotate. The translation member is configured to translate in response to actuation member. The thrust bearing is coupled to the actuation member and includes an inner race, an outer race, and a plurality of balls. The thrust bearing is configured as a zero lead ballscrew, with the inner race integrally formed on the actuation member, and the plurality of balls disposed between the inner and outer races.

Abstract: A position sensing system includes a plurality of two-axis anisotropic magneto-resistive (AMR) sensors to determine the position of a user interface. A magnetic member is coupled to the user interface, which is movable to a position along a random path. The plurality of two-axis AMR sensors is arranged in a two-dimensional sensor array that is spaced apart from the magnetic member. A signal processor circuit is operable to sense the electrical resistance values of each two-axis AMR sensor, to determine the position of the user interface from the resistance values, and to supply position feedback data representative of the determined position.

Abstract: An active control stick assembly is provided. In one embodiment, the active control stick assembly includes a housing assembly, and a control stick support body mounted within the housing assembly for rotation about two substantially orthogonal and co-planar rotational axes. A control stick is fixedly coupled to the control stick support body and rotatable along therewith from a null position to a plurality of control positions. A first spring element is coupled between the housing assembly and the control stick support body and passively biases the control stick toward the null position.

Abstract: A motor control architecture is provided that simultaneously controls multiple motors. The motor control system includes memory, a plurality of motor control processors, and a communication controller. The motor control processors are each responsive to control signals supplied from the communication controller to selectively retrieve system commands and motor positions from the memory, to generate motor commands, and to supply the generated motor commands to the memory. The communication controller selectively receives system commands and transmits the received system commands to the memory, selectively supplies the command signals to selected ones of the motor control processors, selectively receives motor positions from a plurality of motors, selectively transmits motor positions to the memory, selectively retrieves generated motor commands supplied to the memory, and selectively transmits the retrieved motor commands.

Abstract: A flight control surface actuator includes a mechanism that enables the actuator translation member to be selectively decoupled from the actuator rotating member. The actuator includes an actuation member, a translation member, an extension member, and a locking member. The actuation member is adapted to receive a drive force and is configured, in response to the drive force, to rotate and cause the translation member to translate. The extension member surrounds at least a portion of the translation member and is configured to be selectively coupled to, and decoupled from, the translation member. The locking member surrounds at least a portion of the extension tube and is movable between a lock position, in which the locking member couples the extension member to the translation member, and a release position, in which the locking member decouples the extension member from the translation member.

Abstract: An energy storage flywheel system for a spacecraft is implemented with a fully redundant rotating group and gimbal actuator. In particular, the gimbal actuator, motor/generator, primary bearings, and secondary bearing actuator are each implemented with a pair of redundant coils or motors.

Abstract: A flight control surface actuator assembly includes a pair of flight control surface actuators and a pivot arm. One of the flight control surface actuators is coupled to a flight control surface and a static airframe structure, the other flight control surface actuator is coupled to the flight control surface and the pivot arm. The pivot arm coupled to the static airframe structure and is configured to pivot relative to the second flight control surface actuator and the static airframe structure.

Abstract: An aircraft flight control surface actuation system includes a plurality of electric motors-driven flap actuators, and a plurality of electric motor-driven slat actuators. The motor-driven actuators receive activation signals from flap and slat actuator controllers and is, in response to the activation signals, move the flaps and slats between stowed and a deployed positions. The flap and slat actuator controllers each include a plurality of independent actuator control channels that independently supply the activation signals to the motor-driven actuators.

Abstract: A multi-redundant motor may be used to implement a relatively small, lightweight redundant actuator assembly package. The motor is implemented as a brushless DC motor and includes N-number of stators and M-number of rotors. Each stator has a plurality of independent stator coils disposed thereon, and N is an integer greater than two. Each permanent magnet rotor is disposed between, and is spaced axially apart from, two of the stators. Each rotor has a plurality of magnetic dipoles disposed thereon, and M is an integer equal to (N?1).

Abstract: A position sensing system includes a plurality of two-axis anisotropic magneto-resistive (AMR) sensors to determine the position of a user interface. A magnetic member is coupled to the user interface, which is movable to a position along a random path. The plurality of two-axis AMR sensors is arranged in a two-dimensional sensor array that is spaced apart from the magnetic member. A signal processor circuit is operable to sense the electrical resistance values of each two-axis AMR sensor, to determine the position of the user interface from the resistance values, and to supply position feedback data representative of the determined position.

Abstract: A position determination circuit uses the commutation sensor of a brushless DC motor to determine the position of an actuator and/or actuated component 125. The commutation sensor supplies a rotational position signal representative of the rotational position of the motor to a pulse generator. The pulse generator generates a pulse each time the rotational position signal represents a complete revolution of the brushless DC motor. The generated pulses are supplied to an integrator circuit, which selectively supplies a position signal having a voltage magnitude representative of the position of the actuator and/or component.

Abstract: An energy storage flywheel system for a spacecraft is implemented with an electronically redundant power and attitude control system. In particular, the system includes a plurality of flywheels, and a multi-channel processing module and a multi-channel power control module associated with each flywheel. Each multi-channel processing module includes a plurality of controllers that may be operated in either an active or a standby mode, and each multi-channel power control module includes a plurality of power control circuits that may also be operated in either an active or standby mode.

Abstract: An electric motor system includes a motor brake control circuit that uses current induced in the motor stator from generated back EMF to keep the motor brake energized and in its disengaged position, should electric power be lost to the motor system. When the motor has slowed sufficiently that the induced current is no longer sufficient to keep the motor brake energized, the motor brake will move to its engaged position, and prevent further motor rotation. The motor rotational speed at which the motor brake is no longer energized is sufficiently low that any potential degradation or other deleterious effects from motor brake engagement are minimized.

Abstract: A pilot flight control stick haptic feedback mechanism provides variable force feedback to the pilot flight control stick. The flight control stick is movable to a control position in a displacement direction. A motor control unit is operable to selectively supply motor feedback signals to a motor that is coupled to the flight control stick. The motor is responsive to the motor feedback signals to supply a variable feedback force to the flight control stick in a direction that opposes the displacement direction. A passive electromagnetic damping mechanism is electrically coupled to the motor and is at least selectively and passively supplies a non-braking damping force to the flight control stick.

Abstract: An energy storage flywheel system for a spacecraft is implemented with a fully redundant rotating group and gimbal actuator. In particular, the gimbal actuator, motor/generator, primary bearings, and secondary bearing actuator are each implemented with a pair of redundant coils or motors.

Abstract: A submersible vehicle object ejection control system stores a plurality of pump speed command profiles. Each pump speed command profile is based on vehicle depth, vehicle speed, type of object being ejected, maximum noise emission magnitude during object ejection, and object exit velocity. The system also receives data representative of current vehicle depth, current vehicle speed, and the type of object being ejected. In response to these data, the system retrieves one of the plurality of pump speed command profiles and supplies pump speed commands representative of the retrieved pump speed command profile.

Abstract: An electric motor system includes a motor brake control circuit that uses current induced in the motor stator from generated back EMF to keep the motor brake energized and in its disengaged position, should electric power be lost to the motor system. When the motor has slowed sufficiently that the induced current is no longer sufficient to keep the motor brake energized, the motor brake will move to its engaged position, and prevent further motor rotation. The motor rotational speed at which the motor brake is no longer energized is sufficiently low that any potential degradation or other deleterious effects from motor brake engagement are minimized.