An electromechanical actuator was developed that will follow a proportional control command with minimum wasted energy to demonstrate the feasibility of meeting space vehicle actuator requirements using advanced electromechanical concepts. The approach was restricted to a four-channel redundant configuration. Each channel has independent drive and control electronics, a brushless electric motor with brake, and velocity and position feedback transducers. A differential gearbox sums the output velocities of the motors. Normally, two motors are active and the other two are braked.


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    Title :

    Electromechanical Flight Control Actuator, Volume 1


    Publication date :

    1978


    Size :

    169 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English