Candidate pump and driver systems for low thrust cargo orbit transfer vehicle engines which deliver large space structures to geosynchronous equatorial orbit and beyond are evaluated. The pumps operate to 68 atmospheres (1000 psi) discharge pressure and flowrates suited to cryogenic engines using either LOX/methane or LOX/hydrogen propellants in thrust ranges from 445 to 8900 N (100 to 2000 lb F). Analysis of the various pumps and drivers indicate that the low specific speed requirement will make high fluid efficiencies difficult to achieve. As such, multiple stages are required. In addition, all pumps require inducer stages. The most attractive main pumps are the multistage centrifugal pumps.


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    Titel :

    Low-thrust chemical propulsion system pump technology


    Beteiligte:
    Sabiers, R. L. (Autor:in) / Siebenhaar, A. (Autor:in)

    Erscheinungsdatum :

    1981-03-01


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Thrust system technology for solar electric propulsion.

    MASEK, T. D. / PAWLIK, E. V. | AIAA | 1969



    Low-thrust chemical orbit transfer propulsion

    Pelouch, J. J., Jr. | NTRS | 1979