A technology program aimed at improving the performance of low thrust chemical rockets for spacecraft onboard applications is reviewed. Navier-Stokes analyses of low Reynolds number rocket flows have been compared with local flow property measurements obtained using Rayleigh and Raman diagnostics in a 100 N gaseous hydrogen/gaseous oxygen rocket. It is indicated that computational domain should include the near injector flow and that the shear layer combustion model needs improvement. The system analyses and technical efforts intended to develop a technology base for higher performance propellants are presented. A LOX/hydrazine engine is demonstrated to have a 95 percent theoretical c-star which translates into a projected vacuum specific impulse of 345 seconds at an area ratio of 204:1.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Low thrust chemical rocket technology


    Beteiligte:

    Erscheinungsdatum :

    01.08.1992


    Medientyp :

    Aufsatz (Konferenz)


    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 | 1981


    Rocket Thrust Neutralizer

    G. Fountain | NTIS | 1965


    Rocket Thrust Chamber

    E. F. Baehr | NTIS | 1965