Abstract: An auxiliary bearing assembly for selectively engaging a shaft, preferably in an energy storage flywheel system, is configured to include a vibration damping seal, and an axial preload spring. The vibration damping seal damps out vibrations from the rotating group, following engagement of the auxiliary bearing assembly, while the rotating group is spinning down. The axial preload spring absorbs any differential thermal expansion or contraction that may occur between components.

Abstract: An energy storage flywheel system includes a flywheel assembly that is rotationally mounted in a housing assembly, and one or more actuator assemblies. The actuator assemblies are configured to selectively engage and disengage the flywheel assembly. When the actuator assemblies engage the flywheel assembly, the actuator assemblies provide support for, and inhibit rotation of, the flywheel assembly. When the actuator assemblies disengage the flywheel assembly, the actuator assemblies no longer support the flywheel assembly, and no longer inhibit its rotation.

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 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 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.

Abstract: A containment vessel used to enclose an energy storage flywheel system during certification testing of the energy storage flywheel system includes a plurality of concentrically disposed vessels. One or more intermediate shields are freely disposed within an outer shield, and an inner shield is freely disposed within the intermediate shields. The inner shield includes a deflector rim disposed proximate one of its ends that is configured to absorb the energy of ejected material, in the highly unlikely event of a flywheel failure during testing.

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 flight control actuation system comprises a controller, electromechanical actuator and a pneumatic actuator. During normal operation, only the electromechanical actuator is needed to operate a flight control surface. When the electromechanical actuator load level exceeds 40 amps positive, the controller activates the pneumatic actuator to offset electromechanical actuator loads to assist the manipulation of flight control surfaces. The assistance from the pneumatic load assist actuator enables the use of an electromechanical actuator that is smaller in size and mass, requires less power, needs less cooling processes, achieves high output forces and adapts to electrical current variations. The flight control actuation system is adapted for aircraft, spacecraft, missiles, and other flight vehicles, especially flight vehicles that are large in size and travel at high velocities.

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 valve actuator assembly that is implemented in a fully-electric configuration includes two rails and an armature that is moveably disposed between, and electrically coupled to, each of the rails. The armature is configured to couple to a valve element and is moveable between at least a first position and a second position, to thereby move the valve element to at least the open and closed positions, respectively. Upon application of an electrical potential of a first or second polarity across the rails, a current flows through the armature in a first or a second direction, respectively, to thereby generate a Lorentz force. The Lorentz force acts on the armature to move it to the first or second position, and thus move the valve element to the open or closed position, respectively.

Abstract: A device for detecting strain levels imposed on a circuit board includes an apparatus mounted on the circuit board, an amplifier for detecting a change in the impedance of the apparatus and generating an output signal representing the change in the impedance of the apparatus, and a signal conditioner for receiving the output signal and setting the gain of the amplifier.

Abstract: An energy storage flywheel system includes a shaft, one or more primary bearing assemblies, and one or more secondary bearing assemblies. A secondary bearing control circuit determines the operability of the primary bearing assemblies and, based on this determination, selectively engages the secondary bearing assemblies to rotationally support the flywheel shaft.

Abstract: An energy storage flywheel system that includes a power connector extending through the flywheel housing assembly and is hermetically sealed thereto. A circuit board, on which is mounted at least a motor/controller circuit, is coupled to the power connector adjacent to the flywheel housing assembly.

Abstract: An energy storage flywheel system that includes a power connector extending through the flywheel housing assembly and is hermetically sealed thereto. A circuit board, on which is mounted at least a motor/controller circuit, is coupled to the power connector adjacent to the flywheel housing assembly.

Abstract: A flight control actuation system comprises a controller, electromechanical actuator and a pneumatic actuator. During normal operation, only the electromechanical actuator is needed to operate a flight control surface. When the electromechanical actuator load level exceeds 40 amps positive, the controller activates the pneumatic actuator to offset electromechanical actuator loads to assist the manipulation of flight control surfaces. The assistance from the pneumatic load assist actuator enables the use of an electromechanical actuator that is smaller in size and mass, requires less power, needs less cooling processes, achieves high output forces and adapts to electrical current variations. The flight control actuation system is adapted for aircraft, spacecraft, missiles, and other flight vehicles, especially flight vehicles that are large in size and travel at high velocities.

Abstract: A flight control actuation system comprises a controller, electromechanical actuator and a pneumatic actuator. During normal operation, only the electromechanical actuator is needed to operate a flight control surface. When the electromechanical actuator load level exceeds 40 amps positive, the controller activates the pneumatic actuator to offset electromechanical actuator loads to assist the manipulation of flight control surfaces. The assistance from the pneumatic load assist actuator enables the use of an electromechanical actuator that is smaller in size and mass, requires less power, needs less cooling processes, achieves high output forces and adapts to electrical current variations. The flight control actuation system is adapted for aircraft, spacecraft, missiles, and other flight vehicles, especially flight vehicles that are large in size and travel at high velocities.