Abstract
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.
This is a preview of subscription content, log in via an institution to check access.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
Preview
Unable to display preview. Download preview PDF.
References
E. R. G. Eckert and R. M. Drake, Heat and Mass Transfer, McGraw-Hill Inc., New York (1959).
“A Propósal for a Thermal Protection System for a Cryogenic Spacecraft Propulsion Model,” Vol. I, Report GD/A DDB64–018 (March 1964).
C. R. Lindquist, “Linde Company Superinsulation Applied to Space Vehicles,” Revision (December 1, 1962).
Author information
Authors and Affiliations
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 1966 Springer Science+Business Media New York
About this paper
Cite this paper
Getty, R.C., Clay, J.P., Kremzier, E.J., Leonhard, K.E. (1966). Experimental Evaluation of Some Selected Lightweight Superinsulation for Space Vehicles. In: Timmerhaus, K.D. (eds) Advances in Cryogenic Engineering. Advances in Cryogenic Engineering, vol 11. Springer, Boston, MA. https://doi.org/10.1007/978-1-4757-0522-5_5
Download citation
DOI: https://doi.org/10.1007/978-1-4757-0522-5_5
Publisher Name: Springer, Boston, MA
Print ISBN: 978-1-4757-0524-9
Online ISBN: 978-1-4757-0522-5
eBook Packages: Springer Book Archive