Abstract
The Shuttle Obiter entry flight control system (PCS) was designed to meet certain specific performance requirements for given aerodynamics, line replaceable unit (LRU) tolerances, and flight envelopes. Further consideration was given in the design to provide for design assessment requirements under stress conditions. This paper addresses the off-nominal design considerations by providing a definition of the design performance requirements and the conditions under which these requirements are to be met. The approach taken in the classification of the aerodynamic uncertainties are given and the sensitivity of the flight control stability margins to aerodynamics is presented. Finally, the flight control verification process that was undertaken and a comparison of flight test results to predicted performance are discussed.
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