An analytical study evaluating thrust chamber cooling engine cycles and preliminary engine design for low thrust chemical rocket engines for orbit transfer vehicles is described. Oxygen/hydrogen, oxygen/methane, and oxygen/RP-1 engines with thrust levels from 444.8 N to 13345 N, and chamber pressures from 13.8 N/sq cm to 689.5 N/sq cm were evaluated. The physical and thermodynamic properties of the propellant theoretical performance data, and transport properties are documented. The thrust chamber cooling limits for regenerative/radiation and film/radiation cooling are defined and parametric heat transfer data presented. A conceptual evaluation of a number of engine cycles was performed and a 2224.1 N oxygen/hydrogen engine cycle configuration and a 2224.1 N oxygen/methane configuration chosen for preliminary engine design. Updated parametric engine data, engine design drawings, and an assessment of technology required are presented.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Low-thrust chemical rocket engine study


    Beteiligte:
    Shoji, J. M. (Autor:in)

    Erscheinungsdatum :

    1981-03-01


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





    Low-Thrust Chemical Rocket Engine Study

    J. A. Mellish | NTIS | 1981


    Low-thrust chemical rocket engine study

    Mellish, J. A. | NTRS | 1980


    Low-thrust chemical rocket engine study

    Mellish, J. A. | NTRS | 1981