Shuttle vehicle configuration impact on ascent guidance and control

Abstract

This paper discusses the factors leading to the design of the Space Shuttle ascent flight control system. Vehicle constraints on performance, loads, heating, software, and engine gimballing formed the basis for control system requirements and led to configuration and design decisions. Topics discussed include the selection of a thrust vector control capability on the Shuttle solid rocket booster, the control requirements of the solid rocket booster thrust mismatch and misalignment, the Orbiter flight and pad orientation, flight control sensor placement, the ascent load relief system, the elevon load relief system and performance improvements by reduced engine bias angles.