Evaluation of abort capabilities of rocket-powered single-stage-to-orbit launch vehiclesApplication of advanced technologies to future launch vehicle designs would allow the introduction of a rocket-powered, single-stage-to-orbit (SSTO) launch system early in the next century. A fully reusable SSTO vehicle would be quite desirable from an operational standpoint; however, such a vehicle cannot be designed without accompanying technological advances in structure, propulsion, and subsystems. The conceptual design of such a vehicle has recently been completed. This paper examines the abort capabilities of an advanced SSTO launch vehicle which has five main engines. In the event of a single or dual main engine shutdown it was determined when the vehicle could execute return-to-launch-site, abort-to-orbit, or down-range abort maneuvers. Throughout each abort maneuver, vehicle loads are kept within nominal ascent and entry design values.
Document ID
19900032724
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Stanley, Douglas O. (NASA Langley Research Center Hampton, VA, United States)
Powell, Richard W. (NASA Langley Research Center Hampton, VA, United States)