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Risk Assessment and scaling for the SLS LOx ETIn this report we analyze the transpiration cooling by He bubble injection of the long LOx tank feedline heated by the environment heat. We consider possible hazards that can arise in the proposed design of the SLS core stage where the feedline length is much longer than that used in the Space Shuttle.
Document ID
20130008687
Acquisition Source
Ames Research Center
Document Type
Technical Publication (TP)
Authors
Osipov, Viatcheslav V. (Stinger Ghaffarian Technologies, Inc. (SGT, Inc.) Moffett Field, CA, United States)
Hafiychuk, Halyna (Stinger Ghaffarian Technologies, Inc. (SGT, Inc.) Moffett Field, CA, United States)
Devine, Ekaterina V. (Stinger Ghaffarian Technologies, Inc. (SGT, Inc.) Moffett Field, CA, United States)
Khasin, Michael (Stinger Ghaffarian Technologies, Inc. (SGT, Inc.) Moffett Field, CA, United States)
Smelyanskiy, Vadim N. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 27, 2013
Publication Date
December 1, 2012
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NASA/TP-2012-216485
ARC-E-DAA-TN6860
Funding Number(s)
WBS: WBS 00219.001.106.001
CONTRACT_GRANT: NNA08CG83C
Distribution Limits
Public
Copyright
Public Use Permitted.

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