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.
Electromechanical Flight Control Actuator, Volume 1
1978
169 pages
Report
No indication
English
Electromechanical flight control actuator
Tema Archive | 1976
Electromechanical flight control actuator
NTRS | 1976
Electromechanical flight control actuator
NTRS | 1979