Thrust vectoring for single-stage-to-orbit, horizontal takeoff, horizontal landing, space vehiclesThe preliminary design of a horizontal takeoff, horizontal landing, single-stage-to-orbit, rocket-powered space vehicle was performed. The purpose was to examine technology requirements for future small payload launch vehicles. The distinguishing aspect of the design was the utilization of thrust vectoring to provide half of the lift at takeoff. The inclusion of a canard was necessary to provide additional lift at takeoff and to balance the moments produced with thrust vectoring. A weights estimation, an aerodynamic assessment, a trajectory analysis, and a gear weight analysis were performed. The takeoff weight of the resulting vehicle was approximately 1.26 million pounds, based on advanced technology structures and subsystems. The vehicle was designed to deliver a 5000-pound payload to a polar orbit.
Document ID
19860057886
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cunningham, M. J. (NASA Langley Research Center Hampton, VA, United States)
Freeman, D. C., Jr. (NASA Langley Research Center Hampton, VA, United States)
Wilhite, A. W. (NASA Langley Research Center Hampton, VA, United States)
Powell, R. W. (NASA Langley Research Center Hampton, VA, United States)