Lightweight Thermal Protection Systems for Space Vehicle Propellant Tanks

Knoll, R. H.; Oglebay, J. C.

doi:10.4271/640025

Cited by 1 publication

(2 citation statements)

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“…The test tank and cold guard were filled with either liquid hydrogen or liquid nitrogen. The pressure inside the test tank and cold guard were maintiained at 11.376xl0 4 and 11.411x10^ Newtons/ meter^ (16.50 and 16.33 Ib/in2) respectively, by .a back pressure '.control system capable'of controlling pressure to within fl.379 Newtons/meter (0.0002 ib/in^). The test configuration was maintained at these conditions until the bpiloff and sill'strut and shield temperatures stabilized.…”

Section: Procedures mentioning

confidence: 99%

“…[4][5] have been largely confined to idealized, freefloating shields with little effort being devoted either analytically or experimentally to the thermal interaction between shields and their support structures. This paper presents the major results of a program undertaken to (1) develop an analysis which would include the strut-sheild interaction in predicting shadow shield performance, (2) experimentally examine the effect of configuration variables on the performance of a scale model shadow shield system, (3) use the experimental results to verify the analysis.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

An Analytical and Experimental Evaluation of Shadow Shields and Their Support Members

Stochl

Boyle

1973

Advances in Cryogenic Engineering

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Experimental tests were performed on a model shadow shield thermal protection system to examine the effect of certain configuration variables,, The experimental results were used to verify the ability of an analytical program to predict the shadow f> shield performance including the shield-support interaction. In o general, the analysis (assuming diffuse surfaces) agreed well with ' the experimental support temperature profiles. The agreement for the shield profiles was not as good. The results demonstrated (1) shadow shields can be effective in reducing the heat transfer into cryogenic propellant tanks, (2) the conductive heat transfer through supports can be reduced by selective surface coatings.

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Section: Procedures mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%