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Electric orbit transfer vehicle cryogenic propellant system.

Author(s) : SCHUSTER J. R., HUYNH C. T., WILLIAMS G. E.

Type of article: Article

Summary

Study of the propellant storage and supply system for an electric orbit transfer vehicle intended to fly a 168 day spiral trajectory, reveals that the low propellant flow rate needed by the thrusters can be supplied by the boil-off from the storage tank, eliminating the need for any overboard venting. The tank contains a thermodynamic vent system (TVS) for control of tank pressure in zero and low gravity and for supply of propellant to the thrusters. An external compressor, accumulator and regulator condition the hydrogen boil-off provided by the TVS and provide for start-up and shut-down transients. The resulting system is simple, has a very low structural mass fraction and builds on the Centaur cryogenic upper stage technology, which has been operational for over 25 years.

Details

  • Original title: Electric orbit transfer vehicle cryogenic propellant system.
  • Record ID : 1994-0051
  • Languages: English
  • Source: Cryogenics - vol. 33 - n. 4
  • Publication date: 1993/04

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