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Redundancy Management of Shuttle Flight Control Rate Gyroscopes and Accelerometers

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2 Author(s)
H. C. Gelderloos ; Honeywell Inc., Avionics Division, 13350 U.S. Highway 19 South, Clearwater, Florida 33516 ; D. J. Young

The Space Shuttle Flight Control System is required to be two-fault tolerant; i.e., the system must be capable of returning to a landing site even though two system failures occur. This is referred to as fail-operational/fail-safe performance. To achieve this fault tolerance, the avionics equipment is made redundant. A redundancy management (RM) system is required to detect failures and reconfigure the avionics accordingly. This paper describes the Flight Control System (FCS) rate gyro and accelerometer redundancy management design, analysis tools and analysis results.

Published in:

American Control Conference, 1982

Date of Conference:

14-16 June 1982