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Development of a reusable, flight-weight cryogenic foam insulation systemAttention is given to a light weight foam insulation system applicable to reusable cryogenic propellant tankage for hypersonic aircraft and space launch vehicles. The insulation system consists of nominally sized blocks of a high temperature-resistant polymethacrylimide foam that is wrapped with a vapor-impermeable membrane of Kapton-aluminum-Kapton laminate, which is adhesively bonded to the outer propellant tank wall. Test results are presented which indicate that this insulation system is capable of enduring a Mach 5 service environment without structural cracking, deterioration, or loss of performance.
Document ID
19860055874
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mcauliffe, P. S.
(Lockheed-California Co. Burbank, United States)
Davis, R. C.
(Lockheed-California Co. Burbank, CA, United States)
Taylor, A. H.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 12, 2013
Publication Date
June 1, 1986
Subject Category
Launch Vehicles And Space Vehicles
Report/Patent Number
AIAA PAPER 86-1189
Accession Number
86A40612
Distribution Limits
Public
Copyright
Other

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