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Advanced orbit transfer vehicle propulsion system studyA reuseable orbit transfer vehicle concept was defined and subsequent recommendations for the design criteria of an advanced LO2/LH2 engine were presented. The major characteristics of the vehicle preliminary design include a low lift to drag aerocapture capability, main propulsion system failure criteria of fail operational/fail safe, and either two main engines with an attitude control system for backup or three main engines to meet the failure criteria. A maintenance and servicing approach was also established for the advanced vehicle and engine concepts. Design tradeoff study conclusions were based on the consideration of reliability, performance, life cycle costs, and mission flexibility.
Document ID
19860015275
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Cathcart, J. A.
(Martin Marietta Aerospace Denver, CO, United States)
Cooper, T. W.
(Martin Marietta Aerospace Denver, CO, United States)
Corringrato, R. M.
(Martin Marietta Aerospace Denver, CO, United States)
Cronau, S. T.
(Martin Marietta Aerospace Denver, CO, United States)
Forgie, S. C.
(Martin Marietta Aerospace Denver, CO, United States)
Harder, M. J.
(Martin Marietta Aerospace Denver, CO, United States)
Mcallister, J. G.
(Martin Marietta Aerospace Denver, CO, United States)
Rudman, T. J.
(Martin Marietta Aerospace Denver, CO, United States)
Stoneback, V. W.
(Martin Marietta Aerospace Denver, CO, United States)
Date Acquired
September 5, 2013
Publication Date
February 1, 1985
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NAS 1.26:174843
NASA-CR-174843
Accession Number
86N24746
Funding Number(s)
CONTRACT_GRANT: NAS3-23858
PROJECT: RTOP 506-42-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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