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Development of a cryocooler to provide zero boil-off of a cryogenic propellant tank.

Author(s) : FRANK D., ROTH E., OLSON J., et al.

Summary

Lockheed Martin has been developing advanced technology to provide cooling of a cryogenic propellant tank in order to achieve zero boil-off during orbital storage periods. Present systems for long duration flights show large amounts of propellant loss due to parasitic heat loads. A single-stage pulse tube cryocooler has been integrated with a cryogenic methane tank. The cryocooler provides a flow loop of cold gas that circulates in the storage tank and is used to absorb the parasitic heat load, thus allowing the tank to remain non-vented. The cryocooler is located at a distance from the tank, thus requiring a remote cooling loop. The remote cooling loop uses the same working gas as the pulse tube. This flow loop is driven by the same compressor used to provide the pressure wave to the pulse tube cold head, an approach that adds very little complexity to the overall system. The flow loop utilizes steady unidirectional (DC) flow to provide cooling at temperatures near 110 K at the remote cooling location. All cooling is provided by the pulse tube cooler, so that the remote cooling mechanism is forced convection. This paper describes the results from a flow loop developed and tested on a 635-liter cryogenic methane tank as a technology demonstrator. The flow loop, driven by a pulse tube cooler, delivered cold helium gas to and from the remote location to remove the parasitic heat load on the storage tank.

Details

  • Original title: Development of a cryocooler to provide zero boil-off of a cryogenic propellant tank.
  • Record ID : 2008-2408
  • Languages: English
  • Publication date: 2006/06/14
  • Source: Source: Proc. 14th int. Cryocooler Conf., Annapolis, MD
    583-588; fig.; phot.; 3 ref.

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