A space transporter concept is presented in which hydrogen fuelled ramjet propulsion theory is applied to a one and a half stage vertical takeoff and landing hydrogen/oxygen rocket core vehicle with ballistic ascent and descent. A payload to gross liftoff ratio of 10%, i.e., 2.5 times the value of pure rocket systems, is possible, with 56% propellant saving and 44% saving in dry weight. These results can be obtained with existing or near term structures and propulsion systems technology. Ramjet technology can be transferred from missile applications. A small size (155 Mg) reusable space transport system with 15.4 Mg payload in low Earth orbit is feasible.


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    Titel :

    Reusable Air Breathing Ballistic Space Transport Systems


    Beteiligte:
    P. A. Kramer (Autor:in) / R. D. Buehler (Autor:in)

    Erscheinungsdatum :

    1981


    Format / Umfang :

    10 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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