A propulsion system analysis of a dual fuel, dual throat engine for launch vehicle application was conducted. Basic dual throat engine characterization data are presented to allow vehicle optimization studies to be conducted. A preliminary baseline engine system was defined. Dual throat engine performance, envelope, and weight parametric data were generated over the parametric range of thrust from 890 to 8896 KN (200K to 2M lb-force), chamber pressure from 6.89 million to 34.5 million N/sq m (1000 to 5000 psia) thrust ratio from 1.2 to 5, and a range of mixture ratios for the two tripropellant combinations: LO2/RP-1 + LH2 and LO2/LCH4 + LH2. The results of the study indicate that the dual fuel dual throat engine is a viable single stage to orbit candidate.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Dual throat engine design for a SSTO launch vehicle


    Beteiligte:
    Obrien, C. J. (Autor:in) / Salmon, J. W. (Autor:in)


    Erscheinungsdatum :

    1980-03-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    AUTOPHAGE REUSABLE SSTO LAUNCH VEHICLE

    Yemets, Vitaly / Dron', Mykola / Harkness, Patrick | TIBKAT | 2020


    AUTOPHAGE NANOLAUNCHER - A SOLID SSTO LAUNCH VEHICLE

    Yemets, Vitaly / Dron', Mykola / Harkness, Patrick | TIBKAT | 2020


    High Altitude Launch for a Practical SSTO

    Landis, Geoffrey A. / Denis, Vincent | NTRS | 2003


    High Altitude Launch for a Practical SSTO

    Landis, Geoffrey A. / Denis, Vincent / Lyons, Valerie | NTRS | 2003


    High Altitude Launch for a Practical SSTO

    G. A. Landis / V. Denis | NTIS | 2002