Thermal Insulation for Liquid Hydrogen Space Tankage

  • H. M. Tariel
  • J. C. Boissin
  • M. P. Segel
Conference paper
Part of the Advances in Cryogenic Engineering book series (ACRE, volume 12)

Abstract

The thermal insulation for a cryogenic stage is closely related to the intended mission of the space vehicle. For a low-orbit, short-duration flight (less than 1 hr), the thermal insulation is used primarily to restrict the heat flux into propellants induced by kinetic heating while passing through the earth’s atmosphere. When dealing with a final stage, the weight of the non-jettisonable insulation is fully chargeable against the stage payload capability. A drastic optimization must then be carried out, taking into account boil-off losses and cavitation losses at the turbopumps, on the one hand, and insulation weight, on the other hand.

Keywords

Permeability Foam Anhydride Cavitation Calorimeter 

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References

  1. 1.
    D. L. Dearing, in: Advances in Cryogenic Engineering, Vol. 11, Plenum Press, New York (1966), p. 89.CrossRefGoogle Scholar
  2. 2.
    R. L. Middleton, in: Advances in Cryogenic Engineering, Vol. 10, Plenum Press, New York (1965), p. 216.CrossRefGoogle Scholar
  3. 3.
    “Sealed Foam, Constrictive-Wrapped, External Insulation System for LH2 Tanks of Boost Vehicles,” NASA TN D-2685.Google Scholar
  4. 4.
    A. Africano, in : Advances in Cryogenic Engineering, Vol. 5, Plenum Press, New York (1960), p. 533.Google Scholar

Copyright information

© Springer Science+Business Media New York 1967

Authors and Affiliations

  • H. M. Tariel
    • 1
  • J. C. Boissin
    • 1
  • M. P. Segel
    • 1
  1. 1.Centre d’Etudes CryogéniquesSociété l’Air LiquideSassenage, IsèreFrance

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