Plessey Incorporated

Gec-marconi Aerospace Inc.

Smiths Aerospace, Inc.

Smiths Industries Actuation Systems Inc.

Smith Aerospace

Smiths Industries Aerospace Actuation Systems, Inc.

Valentin G Barba

Eugene E Shube

Khoi T Vu

David J Crook

David J C Crook

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 device and an electrical energy storage device 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.

Flight lock actuator with dual energy sources

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.

A boom deploy actuator with improved maintainability and simplicity has an electric motor and control circuitry for selectively powering the motor to develop torque with either rotational direction for rotating a capstan to vary the length of a boom cord extending from the capstan to a boom. In a preferred embodiment, the motor is a brushless electric motor. The control circuitry preferably includes circuit components for limiting the speed of the motor.

Boom deploy system

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.

Membrane-activated hydraulic actuator

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.

Airplane high lift surface drive system

Methods and apparatus for generating a linear vibratory output force having a variable amplitude. The force is generated by the cooperation of four rotating eccentric masses that are grouped in two pairs of two masses. The masses in each pair are counter-rotating (i.e., they rotate at the same speed but in opposite directions). The phase relationship between the two pairs is adjustable. For example, the phase of one pair can be advanced while the phase of the other pair is retarded by an equal amount, thereby changing the amplitude of the output force without changing the direction along which the force acts, and also without changing its frequency if desired.

Vibration control system

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. The same diode is used to dynamically brake the motor when power is removed from the other armature. In both cases the spinning rotor will quickly slow down to facilitate smooth engagement of the positive locking device.

Locking devices and control circuitry for permanent magnet electric

A linear electromechanical actuator has a spring-loaded plunger disposed in a housing. When a solenoid in the housing is energized, the armature of the solenoid moves linearly and, after some initial 'lost' motion, engages and releases the latch mechanism holding the plunger in the housing. The spring associated with the plunger is then free to extend the plunger from the housing. The actuator can be designed so that it is highly immune from unintended actuation due to acceleration of the actuator. The condition of the actuator (e.g., fully cocked or released) can be monitored by switches disposed in the actuator. The actuator can also be constructed to allow manual release as an alternative to release by energization of the solenoid.

Linear electromechanical actuator

An authority limiter includes an input shaft clutched to an output shaft. The output shaft is geared to a motor. Opto-sensors, variable resistors or Hall effect devices provide control signals to a current source supplying power to the motor. Different amounts of opposing torque are applied by the motor dependent upon the positioning of a disc, mechanically attached to the output shaft, that is sensed by the detecting devices. By sensing various angular deviations from a null position, scheduled degrees of torque are applied to the input and output shafts. In another embodiment, the disc is coupled to the output shaft by an auxiliary clutch. When the electrical power is removed from both clutches and the motor, a rotational centering means moves the disc back to a null position with respect to the limiter. Fault monitoring circuitry is provided to disengage the authority limiter when a fault occurs. Finally, solid state switches are provided for interfacing with the aircraft and for enablement of associated devices or satisfactory engagement of the clutch.

Authority limiter

An authority limiter includes an input shaft clutched to an output shaft. The output shaft is geared to a motor. Opto-sensors provide control signals to a current source supplying power to the motor. Different amounts of opposing torque are applied by the motor dependent upon the positioning of a disc, mechanically attached to the output shaft, effecting the optical path in the opto-sensors. In another embodiment, the opto-sensor control is replaced by an electro-mechanical mechanism which senses various thresholds corresponding to angular positions of the coupled input and output shafts.

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Scotrun, PA, United States of America

Valentin G Barba