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.


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    Title :

    Low-Thrust Chemical Rocket Engine Study


    Contributors:
    J. M. Shoji (author)

    Publication date :

    1981


    Size :

    340 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    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