Abstract: A flight lock actuator that can be powered by two sources of stored energy when aircraft power has been switched off. A mechanical energy storage means and an electrical energy storage means provide a fully redundant energy storage system that stores sufficient energy to complete the actuator's extension stroke when aircraft power is removed. The actuator has a motor control system that limits the stroke velocity for both the extension and retraction strokes, including a damper feature capable of effectively braking the actuator during the back-driven extension stroke.

Abstract: A hydraulic actuator that is capable of substantial actuation but does not require a conventional pump, uses only deflectable membranes and passive valves, or, at most, a minimum of active valves, and, under certain circumstances, may be free to move when the actuator is de-energized, is provided. The actuator utilizes the deflectable membranes to move fluid throughout the actuator. The movement of the fluid actuates a shaft or other suitable device, as required.

Abstract: A hydraulic actuator that is capable of substantial actuation but does not require a conventional pump, uses only deflectable membranes and passive valves, or, at most, a minimum of active valves, and, under certain circumstances, may be free to move when the actuator is de-energized, is provided. The actuator utilizes the deflectable membranes to move fluid throughout the actuator. The movement of the fluid actuates a shaft or other suitable device, as required.

Abstract: An airplane high lift surface drive system having a first actuator connected to a first high lift surface and a second actuator connected to a second high lift surface, wherein the first actuator is electrically connected to the second actuator in series.

Abstract: A positive locking device is provided in order to prevent a motor from rotating after power has been removed. The positive locking device has a plate mounted on the motor which engages a disk or hub on the shaft of the motor. In another aspect of the invention, solid state circuitry for switching a permanent magnet motor and providing dynamic braking thereto is provided. The circuitry allows the back EMF generated by the armature coils of a permanent magnet motor to cause a current to flow through the motor when power is removed. This back EMF may be used to help produce smooth engagement of the locking device. In another aspect of the invention, a dynamic braking circuit for a dual armature permanent magnet motor is provided. By applying current to one or the other of two oppositely wound armature coils the motor is made to rotate in either direction. When power is removed from the active armature, this armature is short-circuited through a diode.

Abstract: A positive locking device is provided in order to prevent a motor from rotating after power has been removed. The positive locking device has a plate mounted on the motor which engages a disk or hub on the shaft of the motor. In another aspect of the invention, solid state circuitry for switching a permanent magnet motor and providing dynamic braking thereto is provided. The circuitry allows the back EMF generated by the armature coils of a permanent magnet motor to cause a current to flow through the motor when power is removed. This back EMF may be used to help produce smooth engagement of the locking device. In another aspect of the invention, a dynamic braking circuit for a dual armature permanent magnet motor is provided. By applying current to one or the other of two oppositely wound armature coils the motor is made to rotate in either direction. When power is removed from the active armature, this armature is short-circuited through a diode.