A study to improve the performance of the NASA two-stage-to-orbit vehicle was undertaken. The NASA concept, a horizontal takeoff and landing, fully reusable, two-stage to orbit vehicle, will be capable of launching and returning a 10,000 pound payload to a 100 nmi polar orbit. The vehicle, Beta 2, is a derivative of the USAF/Boeing Beta vehicle which was designed to deliver a 50,000 pound payload to a similar orbit. Beta 2 stages at Mach 6.5 and about 100,000 feet altitude. The propulsion system for the booster is an over/under turbine engine/ramjet configuration. In this paper a study was performed for one of the candidate engines, the variable cycle engine, to assess its potential to meet the required performance needs of the Beta 2 vehicle. Several options for thrust augmentation were studied in order to improve the performance of the engine where there was a critical need. The methodology, constraints, propulsion performance, and mission study results are presented.


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    Titel :

    Options for thrust augmentation for the Beta 2 two-stage-to-orbit launch vehicle


    Beteiligte:
    Jules, Kenol (Autor:in)

    Erscheinungsdatum :

    1993-12-01


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch







    Thrust Augmentation Options for the Beta II Two-Stage-to-Orbit Vehicle

    Snyder, C. A. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 1993