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Propulsion requirements for reusable single-stage-to-orbit rocket vehiclesThe conceptual design of a single-stage-to-orbit (SSTO) vehicle using a wide variety of evolutionary technologies has recently been completed as a part of NASA's Advanced Manned Launch System (AMLS) study. The employment of new propulsion system technologies is critical to the design of a reasonably sized, operationally efficient SSTO vehicle. This paper presents the propulsion system requirements identified for this near-term AMLS SSTO vehicle. Sensitivities of the vehicle to changes in specific impulse and sea-level thrust-to-weight ratio are examined. The results of a variety of vehicle/propulsion system trades performed on the near-term AMLS SSTO vehicle are also presented.
Document ID
19950037618
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Stanley, Douglas O.
(NASA Langley Research Center Hampton, VA, United States)
Engelund, Walter C.
(NASA Langley Research Center Hampton, VA, United States)
Lepsch, Roger
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
May 1, 1994
Publication Information
Publication: Journal of Spacecraft and Rockets
Volume: 31
Issue: 3
ISSN: 0022-4650
Subject Category
Spacecraft Propulsion And Power
Accession Number
95A69217
Distribution Limits
Public
Copyright
Other

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