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Experiences with Pressurized Discharge of Liquid Oxygen from Large Flight Vehicle Propellant Tanks

  • M. E. Nein
  • R. R. Head
Part of the Advances in Cryogenic Engineering book series (ACRE, volume 7)

Abstract

Liquid propellant missiles and space vehicles require pressurization of the propellant containers during flight to provide sufficient net positive suction head for the pumps and structural rigidity for the tanks. It is important in this application that the pressurization system be of light weight and that it use a pressurant compatible with the propellant. The problem of determining the pressurant requirements for cryogenic propellants is being studied extensively by various groups in the cryogenics and rocket vehicle field. Mathematical models describing the internal thermodynamics of pressurization systems are being devised for this purpose. Unfortunately, most of the experimental studies are confined to small-model tests, the results of which have to be applied to tank systems several orders larger in capacity.

Keywords

Tank Wall Container Wall Tank System Model Tank Liquid Oxygen 
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References

  1. 1.
    University of Michigan, Engineering Research Institute for Department of the Army, Detroit Ordnance District Contract No. DA-20–018-ORD-15316.Google Scholar
  2. 2.
    NASA, Lewis Research Center, private communication.Google Scholar
  3. 3.
    D. C. Bowersock, R.W. Gardner, and R. C. Reid in Advances in Cryogenic Engineerings Vol. 4, K. D. Timmerhaus (ed.), Plenum Press, Inc. (1960), p. 342.Google Scholar
  4. 4.
    “Atmospheric Heat Transfer to Vertical Tanks Filled with Liquid Oxygen,” Arthur D. Little, Inc. (November 1, 1958).Google Scholar

Copyright information

© Springer Science+Business Media New York 1962

Authors and Affiliations

  • M. E. Nein
    • 1
  • R. R. Head
    • 1
  1. 1.George C. Marshall Space Flight CenterNational Aeronautics and Space AdministrationHuntsvilleUSA

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