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.
A portion of the test program was funded under NASA Lewis Research Center Contract NAS 3–4199.
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Reference
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).
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© 1966 Springer Science+Business Media New York
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Parmley, R.T., Elgin, D.R., Coston, R.M. (1966). Shingle Multilayer Insulation for Space Vehicles Using Cryogenic Fluids. 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_3
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DOI: https://doi.org/10.1007/978-1-4757-0522-5_3
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