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Advanced technologies for rocket single-stage-to-orbit vehiclesA single-stage-to-orbit vertical takeoff/horizontal landing rocket vehicle was studied to determine the benefits of advanced technology. Advanced technologies that were included in the study were variable mixture ratio oxygen/hydrogen rocket engines and materials, structures, and subsystem technologies currently being developed in the National Aero-Space Plane Program. The application of advanced technology results in an 85 percent reduction in vehicle dry weight. With advanced materials, an external thermal protection system, like the Space Shuttle tiles, was not required. Compared to an all-airbreathing horizontal takeoff/horizontal landing vehicle using the same advanced technologies and mission requirements, the rocket vehicle is lighter in dry weight and has fewer subsystems. To increase reliability and safety, operational features were included in the rocket vehicle-robust subsystems, 5 percent additional margin, no slush hydrogen, fail-operational with an engine out, and a crew escape module. The resulting vehicle grew in dry weight and was still lower in dry weight than the airbreathing vehicle.
Document ID
19910034727
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wilhite, Alan W.
(NASA Langley Research Center Hampton, VA, United States)
Bush, Lance B.
(NASA Langley Research Center Hampton, VA, United States)
Cruz, Christopher I.
(NASA Langley Research Center Hampton, VA, United States)
Lepsch, Roger A.
(NASA Langley Research Center Hampton, VA, United States)
Morris, W. Douglas
(NASA Langley Research Center Hampton, VA, United States)
Stanley, Douglas O.
(NASA Langley Research Center Hampton, VA, United States)
Wurster, Kathryn E.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1991
Subject Category
Launch Vehicles And Space Vehicles
Report/Patent Number
AIAA PAPER 91-0540
Accession Number
91A19350
Distribution Limits
Public
Copyright
Other

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