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Cyclic Cryogenic Thermal-Mechanical Testing of an X-33/RLV Liquid Oxygen Tank ConceptAn important step in developing a cost-effective, reusable, launch vehicle is the development of durable, lightweight, insulated, cryogenic propellant tanks. Current cryogenic tanks are expendable so most of the existing technology is not directly applicable to future launch vehicles. As part of the X-33/Reusable Launch Vehicle (RLV) Program, an experimental apparatus developed at the NASA Langley Research Center for evaluating the effects of combined, cyclic, thermal and mechanical loading on cryogenic tank concepts was used to evaluate cryogenic propellant tank concepts for Lockheed-Martin Michoud Space Systems. An aluminum-lithium (Al 2195) liquid oxygen tank concept, insulated with SS-1171 and PDL-1034 cryogenic insulation, is tested under simulated mission conditions, and the results of those tests are reported. The tests consists of twenty-five simulated Launch/Abort missions and twenty-five simulated flight missions with temperatures ranging from -320 F to 350 F and a maximum mechanical load of 71,300 lb. in tension.
Document ID
19990094229
Document Type
Technical Memorandum (TM)
Authors
Rivers, H. Kevin
(NASA Langley Research Center Hampton,VA United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1999
Subject Category
Launch Vehicles And Space Vehicles
Report/Patent Number
NASA/TM-1999-209560
NAS 1.15:209560
L-17818
Funding Number(s)
PROJECT: RTOP 242-23-02-13
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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