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Development of Rene' 41 honeycomb structure as an integral cryogenic tankage/fuselage concept for future space transportation systemsThe status of the structural development of an integral cryogenic-tankage/hot-fuselage concept for future space transportation systems (STS) is discussed. The concept consists of a honeycomb sandwich structure which serves the combined functions of containment of cryogenic fuel, support of vehicle loads, and thermal protection from an entry heating environment. The inner face sheet is exposed to a cryogenic (LH2) temperature of -423 F during boost; and the outer face sheet, which is slotted to reduce thermal stress, is exposed to a maximum temperature of 1400 F during a high altitude, gliding entry. A fabrication process for a Rene' 41 honeycomb sandwich panel with a core density less than 1 percent was developed which is consistent with desirable heat treatment processes for high strength.
Document ID
19820022452
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Shideler, J. J. (NASA Langley Research Center Hampton, VA, United States)
Swegle, A. R. (Boeing Aerospace Co. Seattle, United States)
Fields, R. A. (NASA Dryden Flight Research Center)
Date Acquired
September 4, 2013
Publication Date
June 1, 1982
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NAS 1.15:83306
NASA-TM-83306
AIAA PAPER 82-0653
Accession Number
82N30328
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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