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Feasibility analysis of cislunar flight using the Shuttle OrbiterA first order orbital mechanics analysis was conducted to examine the possibility of utilizing the Space Shuttle Orbiter to perform payload delivery missions to lunar orbit. In the analysis, the earth orbit of departure was constrained to be that of Space Station Freedom. Furthermore, no enhancements of the Orbiter's thermal protection system were assumed. Therefore, earth orbit insertion maneuvers were constrained to be all propulsive. Only minimal constraints were placed on the lunar orbits and no consideration was given to possible landing sites for lunar surface payloads. The various phases and maneuvers of the mission are discussed for both a conventional (Apollo type) and an unconventional mission profile. The velocity impulses needed, and the propellant masses required are presented for all of the mission maneuvers. Maximum payload capabilities were determined for both of the mission profiles examined. In addition, other issues relating to the feasibility of such lunar shuttle missions are discussed. The results of the analysis indicate that the Shuttle Orbiter would be a poor vehicle for payload delivery missions to lunar orbit.
Document ID
19910014907
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Haynes, Davy A. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1991
Subject Category
Space Transportation
Report/Patent Number
NASA-TM-104084
NAS 1.15:104084
Accession Number
91N24220
Funding Number(s)
PROJECT: RTOP 594-81-12-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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