Experimental Evaluation of Some Selected Lightweight Superinsulation for Space Vehicles
The use of high-energy cryogenic fuels has imposed demands for effective design and application of superinsulation for advanced tank designs. The high effectiveness of multilayer superinsulations is achieved by a series of’ radiation shields of low emissivity. The shields may be separated by insulating spacers under a pressure below 10-5 mm Hg absolute. During ground hold and boost, the insulation is exposed to the atmosphere unless it is sufficiently shrouded. This paper will not discuss these transient conditions, but rather will be concerned only with the subsequent space performance.
KeywordsHeat Flux Contact Resistance Space Vehicle Concentric Layer Radiation Shield
Unable to display preview. Download preview PDF.
- 1.E. R. G. Eckert and R. M. Drake, Heat and Mass Transfer, McGraw-Hill Inc., New York (1959).Google Scholar
- 2.“A Propósal for a Thermal Protection System for a Cryogenic Spacecraft Propulsion Model,” Vol. I, Report GD/A DDB64–018 (March 1964).Google Scholar
- 3.C. R. Lindquist, “Linde Company Superinsulation Applied to Space Vehicles,” Revision (December 1, 1962).Google Scholar