A near-term technology launch system is described in which Space Shuttle main engines are used on a manned orbiter and also on twin strap-on unmanned boosters. The orbiter has a circular body and clipped delta wings. The twin strap-on boosters have a circular body and deployable oblique wings for a glideback recovery. The dry and gross weights of the system, capable of delivering 70 klb of cargo to orbit, are compared with a similar system with hydrocarbon-fueled boosters and with the current Shuttle.


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    Titel :

    Two-Stage Reusable Launch System Utilizing a Winged Core Vehicle and Glideback Boosters


    Beteiligte:
    I. O. Macconochie (Autor:in) / J. A. Martin (Autor:in) / J. S. Wood (Autor:in) / M. O. Duquette (Autor:in)

    Erscheinungsdatum :

    1989


    Format / Umfang :

    21 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Two-stage reusable launch system utilizing a winged core vehicle and glideback boosters

    Macconochie, Ian O. / Martin, James A. / Wood, James S. et al. | NTRS | 1989





    REUSABLE LAUNCH VEHICLE STAGE

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    Freier Zugriff