Abstract Lockheed Martin has developed a high power version of its mini pulse tube cryocooler to provide an increased cooling capacity (2.7 W at 80 K). This unit was developed under contract to the European Space Center (ESA) as a potential backup for their INTEGRAL experiment. The design approach was to utilize the compressor system from a previously developed mini pulse tube system and increase piston size for higher swept volume and re-optimize the cold head for higher cooling capability. Prior development at LM proved the viability of this approach under company funded and DARPA funded programs. An engineering model of both the cryocooler and its drive electronics was developed and tested at LM, then delivered to ESA for their test program. This paper summarizes the system characteristics and presents the results of test programs at both LM and ESA.


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    Titel :

    Development of a Lightweight Pulse Tube Cryocooler for Space Applications


    Beteiligte:
    Nast, T. (Autor:in) / Olson, J. (Autor:in) / Champagne, P. (Autor:in) / Evtimov, B. (Autor:in) / Renna, Todd (Autor:in) / Sarri, G. (Autor:in) / Gomez Hernandez, C. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2003-01-01


    Format / Umfang :

    8 pages




    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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