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Propellant Tank Pressurization-System Analysis

  • A. M. Momenthy
Part of the Advances in Cryogenic Engineering book series (ACRE, volume 9)

Abstract

A computer program has been formulated as a tool for conducting design analyses of missile propellant-tank pressurization systems. In contrast to analysis methods developed for a specific system model [1–8], this program was developed to handle the general case. To meet this objective, some theoretical rigor was sacrificed for application flexibility. In order to indicate the effects of this method, computer analysis predictions are compared with data obtained from a liquid-hydrogen pressurlzation-system test program.

Keywords

Heat Transfer Tank Wall Vehicle Acceleration Enthalpy Balance Heat Transfer Relation 
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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References

  1. 1.
    D. C. Bowersock Jr., and R. C. Reid, in Advances in Cryogenic Engineering, Vol. 6, Plenum Press, New York (1960), p. 261.Google Scholar
  2. 2.
    V. S. Arpaci, J. A. Clark, and W. O. Winer, in Advances in Cryogenic Engineering, Vol. 6, Plenum Press, New York (1960), p. 310.Google Scholar
  3. 3.
    “Main Propellant Tank Pressurlzation System Study and Test Program,” Lockheed-Georgia Co., Final Report ER-5296, Vol. IV (December 1961).Google Scholar
  4. 4.
    H. S. Carslaw and J. C. Jaeger, Conduction of Heat in Solids, Oxford, The Clarendon Press, London (1959), p. 50.Google Scholar
  5. 5.
    M. E. Nein and R. R. Head, in Advances in Cryogenic Engineering, Vol. 7, Plenum Press, New York (1961), p. 244.Google Scholar

Copyright information

© Springer Science+Business Media New York 1964

Authors and Affiliations

  • A. M. Momenthy
    • 1
  1. 1.The Boeing CompanySeattleUSA

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