Engine cycle analyses conducted on a 3000-lbf component testing model of an H2/O2-fueled advanced orbit-transfer vehicle engine employing a dual-expander cycle have yielded pressure and temperature trend predictions. On the basis of the results obtained, the dual-expander cycle is projected to be scalable to thrust levels of as much as 50,000 lbf, with chamber pressures of 2000 psi. The high chamber pressure, in conjunction with the use of a gas-gas injector element, facilitates 10:1-range continuously variable throttling. The preferred thrust level for supporting mission studies would be of the order of 20,000 lbf.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Advanced H2/O2 space engine parametrics


    Beteiligte:

    Erscheinungsdatum :

    1989-07-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Advanced H2/O2 space engine parametrics

    SCHNEIDER, J. | AIAA | 1989


    Parametrics CAD can!

    Ankeny,G.L. / Parametric,US | Kraftfahrwesen | 1992



    Maglev Cost and Performance Parametrics

    Deutsch, L. | British Library Conference Proceedings | 1993


    Parametrics of Nickel-hydrogen Cell Design

    Denoncourt, Peter J. / Hall, Arnold M. | AIAA | 1987