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Thermal performance of multilayer insulationsExperimental and analytical studies were conducted in order to extend previous knowledge of the thermal performance and gas evacuation characteristics of three selected multilayer insulation (MLI) composites. Flat plate calorimeter heat flux measurements were obtained for 20- and 80- shield specimens using three representative layer densities over boundary temperatures ranging from 39 K (70 R) to 389 K (700 R). Laboratory gas evacuation tests were performed on representative specimens of each MLI composite after initially purging them with helium, nitrogen, or argon gases. In these tests, the specimens were maintained at temperatures between 128 K (230 R) and 300 K (540 R). Based on the results of the laboratory-scale tests, a composite MLI system consisting of 112 unperforated, double-aluminized Mylar reflective shields and 113 water preconditioned silk net spacer pairs was fabricated and installed on a 1.22-m-(4-ft-) diameter calorimeter tank.
Document ID
19740014451
Document Type
Contractor Report (CR)
Authors
Keller, C. W. (Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Cunnington, G. R. (Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Glassford, A. P. (Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Date Acquired
September 3, 2013
Publication Date
April 5, 1974
Subject Category
THERMODYNAMICS AND COMBUSTION
Report/Patent Number
NASA-CR-134477
LMSC-D349866
Funding Number(s)
CONTRACT_GRANT: NAS3-14377
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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