Heat Exchanger Design for Cryogenic Propellant Tanks
The design of efficient thermal control systems for cryogenic vehicles becomes exceedingly difficult as mission time is increased. The simple addition of insulation is not always an optimum approach since many of the longer earth orbit and interplanetary missions will continue to demand that the propellant tank be vented. Because the Tented propellant is at a low-energy state, the possibility of utilizing its available refrigeration to increase Yehicle performance arises.
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- 1.G. W. Burge, “System Effects on Propeliant Storability and Vehicle Performance,” Douglas Aircraft Company, Inc., DAC-S9314, Final Tech. Report AFRPL-TR-66–253 (Oct. 1966).Google Scholar
- 2.W. H. Sterbentz, “Liquid Propeliant Thermal Conditioning System,” First Quarterly Progress Report, LMSC-A819763, Lockheed Missiles and Space Co., Sunnyvale, Calif. (May 15, 1966).Google Scholar
- 3.R. P. Warren and J. W. Anderson, in: Advances in Cryogenic Engineering, Vol. 12, Plenum Press, New York (1967), p. 63.Google Scholar
- 4.P. J. Schneider, “Conduction Heat Transfer,” Addison-Wesley Publishing Co., Inc., Reading, Mass. (1957).Google Scholar