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: A pilot flight control stick haptic feedback mechanism provides variable force feedback to the pilot flight control stick based on actual aircraft conditions. The flight control stick is movable to a control position in a displacement direction. A control unit receives one or more signals representative of aircraft conditions and, in response thereto, selectively supplies a variable force feedback signal. A magnetic bearing is disposed adjacent at least a portion of the flight control stick, and is responsive to the variable force feedback signal to supply a variable magnetic feedback force to the flight control stick in a direction that opposes the displacement direction.

Abstract: A smart power conversion and control system and method converts source AC power at a first voltage level to DC power at a second voltage level that is less than the first voltage level. Upon receipt of a command signal, a portion of the system is enabled to further convert the source AC power to regulated DC power at a voltage level that is less than the first voltage level and greater than the second voltage level. One or more relatively high voltage DC loads are then energized with the regulated DC power. When the portion of the system is not enabled, the source AC power is not converted.

Abstract: An aircraft flight control surface actuation system includes a plurality of flap actuators, and a plurality of slat actuators. The actuators receive actuator position commands from an actuator control unit and, in response, move flaps and slats between stowed and deployed positions. The flight control surface actuator control unit includes a plurality of independent actuator control channels. One or more of the independent actuator control channels is coupled to both a flap actuator and a slat actuator, and is configured to selectively supply the actuator position commands thereto.

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: 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: A flight control surface actuation system, and the method implemented thereby, prevents an asymmetric secondary flight control surface deploy situation in the unlikely event one or more of the secondary flight control surfaces becomes inoperable. The system includes a control unit that receives one or more signals representative of operability of each of the secondary flight control surfaces. In response to these signal, the control unit determines the operability of each of the flight control surfaces and, upon determining that a flight control surface on one of the aircraft wings is inoperable, automatically moves, or inhibits movement of, one or more symmetric flight control surfaces on the other aircraft wing.

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: A charging system for an unmanned underwater vehicle (UUV) is disposed within a submerged docking station. The charging system includes a battery, a fuel cell, a fuel source, and a charge controller. The battery supplies electrical power to an electrical distribution bus in the docking station. The charge controller monitors the charge state of the battery and, when needed, activates the fuel cell to recharge the battery. The charge controller also activates the fuel cell when a UUV is docked in the docking station for recharging of its power plant.

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 electric flight control surface actuation system is implemented using a low level control section and a high power section. The low level control section is disposed within an electronics bay within the aircraft, and is in operable communication with one or more flight computers via a communication bus. The flight computers supply flight control surface position commands to the low level control section, which in turn transmits actuator commands to the high power section via a plurality of redundant communication links. The high power section is disposed remotely from the low level control section and, in addition to being in operable communication with the low level control section, is coupled to an aircraft power bus and to each of the actuators. The high power section receives the actuator position commands transmitted from the low level control section and, in response, selectively energizes the actuators from the aircraft power bus.

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: An integrated power and attitude control system and method for a vehicle efficiently supplies electrical power to both low voltage and high voltage loads, and does not rely on relatively heavy batteries to supply power during the vehicle initialization process. The system includes an energy storage flywheel, and a solar array that is movable between a stowed position and a deployed position. The energy storage flywheel is spun up, using electrical power supplied from a low voltage power source, to a rotational speed sufficient to provide attitude control. Then, after the solar array is moved to its deployed position, the energy storage flywheel is spun up, using electrical power supplied from a second power source, to a rotational speed sufficient to provide both attitude control and energy storage.

Abstract: A flight control surface actuator assembly includes a plurality of flight control surface actuators, and a pivot arm. Each flight control surface actuator is adapted to couple to a flight control surface, and each is further adapted to receive a drive force and is operable, upon receipt thereof, to move between at least an extended position and a retracted position. The pivot arm is rotationally coupled to, and is configured to pivot relative to, each of the flight control surface actuators, the pivot arm is also adapted to be rotationally coupled to, and configured to pivot relative to, a static airframe structure.

Abstract: A magnetic bearing sensing and control system and method provides increased tolerance to faults associated with the associated displacement sensors. The system includes a plurality of redundant displacement sensor sets to provide dual or triple displacement sensor redundancy, or higher if desired, and implements a process for determining when one or more displacement sensors is faulty. The system also compensates for determined sensor-related faults.

Abstract: A charging system for an unmanned underwater vehicle (UUV) is disposed within a submerged docking station. The charging system includes a battery, one or more generators, and a charge controller. The battery supplies electrical power to an electrical distribution bus in the docking station. The charge controller monitors the charge state of the battery and, when needed, activates one or more of the generators to recharge the battery. The charge controller also activates one or more of the generators when a UUV is docked in the docking station for recharging of its power plant.

Abstract: A health monitoring system for an unmanned underwater vehicle (UUV) is disposed within a submerged docking station. The health monitoring system receive signals representative of performance of the docking station equipment and uses the data to determine the health status of the docking station equipment, to generate health status data representative thereof, and transmits the health status data to a remote station. The health monitoring system also retrieves health status data from UUVs that are periodically docked in the docking station, and transmits this data to the remote station.

Abstract: A docking station for an unmanned underwater vehicle (UUV) includes a tether control system to minimize movement of the docking station when the UUV is docking therein. The docking station is a submerged station that is tethered to a floating structure via a tether line. The tether control system selectively loosens and tightens the tether line during UUV docking, to thereby minimize movement of the docking station during UUV docking operations.

Abstract: A fluid-powered actuator assembly is modified to include a low power generator. The low power generator rotates in response to a drive force received from the actuator assembly, and thus only generates electrical power when the actuator assembly is operating. The low power generator is used to supply electrical power to various sensors and circuits, which may be used to implement prognostic and health monitoring capabilities for the actuator assembly.

Abstract: A system and method for removing energy from the rotating group in an energy storage flywheel system during flywheel system testing includes one or more sensors is operable to sense operational parameters of the energy storage flywheel and to supply a sensor signals representative thereof. A primary control circuit is coupled to receive the sensor signals and, in response thereto, selectively supplies a primary brake activation signal to a brake. The brake, in response to the brake activation signal, selectively supplies a brake force to the energy storage flywheel.