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)