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Shingle Multilayer Insulation for Space Vehicles Using Cryogenic Fluids

  • R. T. Parmley
  • D. R. Elgin
  • R. M. Coston
Part of the Advances in Cryogenic Engineering book series (ACRE, volume 11)

Abstract

An efficient multilayer thermal protection system design is necessary for the successful development of spacecraft using cryogenic propellants for mission durations of more than a day. This design must satisfy the requirements peculiar to the mission and perform satisfactorily when subjected to the often contradictory demands of ground hold, ascent, and space environments.

Keywords

Thermal Performance Lateral Thermal Conduction Effective Shield Thermal Protection System Solid Conduction 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Reference

  1. 1.
    E. M. Sparrow, “Radiant Emission, Absorption, and Transmission Characteristics of Cavities and Passages,” Symposium on Thermal Radiation of Solids, Session I, San Francisco, California (March 4, 1964).Google Scholar

Copyright information

© Springer Science+Business Media New York 1966

Authors and Affiliations

  • R. T. Parmley
    • 1
  • D. R. Elgin
    • 1
  • R. M. Coston
    • 1
  1. 1.Lockheed Missiles and Space CompanySunnyvaleUSA

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