A sensitivity analysis of the factors which affect a successful abort maneuver following a space shuttle launching is presented. Wind tunnel tests were conducted using optimum simulation techniques and data acquisition procedures. Static stability, dynamic stability, and local loads were investigated. It is concluded that parallel abort separation of the space shuttle components is possible at both high and low dynamic pressures. Successful separation is dependent upon configuration, Mach number, rocket exhaust impingement and relative position and attitude of the stages.
Abort separation of the shuttle
1972-02-01
Conference paper
No indication
English
NTIS | 2011
|AIAA | 2011
|British Library Conference Proceedings | 2011
|NTRS | 2011
|Space shuttle ascent phase abort considerations
NTRS | 1970
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