The Space Shuttle flight control system (FCS) is a digital fly-by-wire system that provides vehicle stability, response, and handling qualities necessary to return safely from orbit, ending with a pinpoint landing on a 300 by 15,000-foot (90 by 4,600-meter) runway. Furthermore, on its first flight, it had to fly successfully the entire envelope-manned. Thus, the FCS was subjected to one of the most extensive programs of certification by analysis and simulation ever conducted. An overview of the entry and landing FCS is presented along with the requirements and considerations used in the design process. The network of simulation programs used in the FCS design and verification are addressed. The flight test results and the current issues related to landing and roll-out are presented.
Space Shuttle Descent Flight Verification by Simulation: A Challenge in Implementing Flight Control System Robustness
1990
17 pages
Report
No indication
English
Verification of the Space Shuttle ascent flight control
NTRS | 1980
|Space Shuttle flight control system
NTRS | 1975
|Space shuttle digital flight control system
NTRS | 1976
|The Space Shuttle ascent flight control system
AIAA | 1976
|NTRS | 1982
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