Results of launch-vehicle mission analysis are presented; launch vehicles studied consist of hypersonic aircraft first stages, powered by hydrogen-fueled, subsonic-burning turboramjets, and H2-O2 rocket second stages; parametric investigation of vehicle characteristics and trajectory is presented and used to indicate maximum payload capability of launch systems; results indicate that launch vehicles are characterized by lower fuselage volumes and higher wing loadings than those associated with hypersonic transport, but only small penalties result from using transport-like characteristics for launch vehicles.


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    Title :

    Some comparisons of turboramjet-powered hypersonic aircraft for cruise and boost missions


    Additional title:

    J Aircraft


    Contributors:

    Published in:

    Publication date :

    1966


    Size :

    8 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    Some comparisons of turboramjet-powered hypersonic aircraft for cruise and boost missions.

    GREGORY, T. J. / PETERSEN, R. H. / SMITH, C. L. | AIAA | 1966


    Some comparisons of turboramjet-powered hypersonic aircraft for cruise and boost missions.

    Gregory, T. J. / Petersen, R. H. / Smith, C. L. | NTRS | 1965



    Some comparisons of turboramjet-powered hypersonic aircraft for cruise and boost missions.

    Gregory, T. J. / Petersen, R. H. / Smith, C. L. | NTRS | 1966


    Turboramjet propulsion for hypersonic booster-aircraft of TSTO aerospace system

    Lanshin, A. / Dulepov, N. / Zakharov, N. et al. | AIAA | 1996