The requirements for mechanisms used in the Space Transportation System (STS) are to provide dual fault tolerance, and if the payload equipment violates the Shuttle bay door envelope, these deployment/restow mechanisms must have independent primary and backup features. The research and development of an electromechanical actuator that meets these requirements and will be used on the Transfer Orbit Stage (TOS) program is described.
A dual, fault-tolerant aerospace actuator
1985-08-01
Conference paper
No indication
English
A fault tolerant implementation for aerospace
AIAA | 1993
|A Fault Tolerant Implementation for Aerospace
British Library Conference Proceedings | 1993
|