Sensitivity of power plant mass to such variables as vehicle thrust requirements, precompression surface incidence, intake and nozzle designs and turbo machinery design constraints is described for an example of turboramjet power plant propelling the first stage of a two stage to orbit launcher. The propulsion system consisted of a turbojet engine behind a rectangular ramp intake with the reheat system operating as a ramjet burner for flight beyond approximately Mach 3. The core engine was isolated from the airflow at these conditions. Several of the aspects of overall vehicle performance are described where these interact with the power plant design, and the influence of mission definition on power plant optimization is discussed.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Parametric Assessment of Propulsion System Mass for Airbreathing Launcher Configurations


    Beteiligte:
    F. A. Hewitt (Autor:in) / R. R. Schwab (Autor:in)

    Erscheinungsdatum :

    1989


    Format / Umfang :

    7 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Aerodynamics for Optimal Engine-Integrated Airbreathing Launcher Configurations

    Lewis, Mark / Boyd, I. / Cockrell, Charles | AIAA | 2004


    Aerodynamics for Optimal Engine-Integrated Airbreathing Launcher Configurations

    Lewis, M. J. / Boyd, I. D. / Cockrell, C. E. et al. | British Library Conference Proceedings | 2004


    Propulsion system for airbreathing launcher in the French PREPHA Program

    Rothmund, Christophe / Scherrer, Dominique / Levy, Frederic et al. | AIAA | 1996


    Propulsion System for Airbreathing Launcher in the French PREPHA Program

    Rothmund, C. / Scherrer, D. / Bouchez, M. et al. | British Library Conference Proceedings | 1996


    Airbreathing space launcher interest of a fully variable geometry propulsion system

    Bouchez, Marc / Levine, Vadim / Falempin, Francois et al. | AIAA | 1998