The ability of the space shuttle to deliver and service payloads is enhanced by assuring abort capability during ascent for safe return of the vehicle and crew in the event of a serious malfunction. A vast array of systems failures including space shuttle main engine (SSME) failures is considered, resulting in detailed technical analyses and the design of powered flight abort trajectories.
The discussion will include specific guidance functions and trajectory design of return to launch site (RTLS) and transoceanic abort landing (TAL) intact abort profiles. Also to be discussed is the increasing emphasis on contingency (multiple main engine failure) aborts.
