Abstract Lockheed Martin’s Advanced Technology Center (LM ATC) has developed a miniature, lightweight pulse tube cryocooler system for space operation under funding from NASA/GSFC. The cold end is a U-tube configuration, and is driven by a dual opposed piston flexure bearing compressor. The compressor utilizes a moving magnet linear motor and incorporates a number of features that simplify assembly and enhance reliability. This cooler is designed for 0.3 W of cooling at 65 K with a 310 K rejection temperature, 15 W of compressor power, and a mass of less than 1.25 kg. Three engineering model cryocoolers are to be delivered to NASA/GSFC. Two have been completed and test data is presented here on the EM performance. In a parallel effort, we have developed a lightweight, power efficient electronic controller funded by LM ATC cost sharing funds for a DARPA contract. The first Engineering Model of this controller has been completed and functional testing has verified successful operation. All of the design goals have been met or exceeded.


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    Titel :

    Miniature Pulse Tube Cryocooler for Space Applications


    Beteiligte:
    Nast, T. C. (Autor:in) / Champagne, P. J. (Autor:in) / Kotsubo, V. (Autor:in) / Olson, J. (Autor:in) / Collaco, A. (Autor:in) / Evtimov, B. (Autor:in) / Renna, T. (Autor:in) / Clappier, R. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.01.2002


    Format / Umfang :

    10 pages




    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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