A hypersonic airbreathing missile, using dual mode scramjet engines for propulsion, is described. The fuselage is constructed of a material with a high heat sink capacity and is covered with a thermal protective shield and lined with an internal insulating blanket. The engine airframe integration uses the flat lower portion of the lower fuselage to precompress the air entering the scramjet engines. The precompression of air entering the scramjet inlets increases as the angles of attack. This feature results in a highly maneuverable missile which can accelerate as it banks into a turn.


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    Titel :

    Hypersonic Airbreathing Missile


    Beteiligte:
    J. L. Hunt (Autor:in) / P. L. Lawing (Autor:in) / D. C. Marcum (Autor:in)

    Erscheinungsdatum :

    1978


    Format / Umfang :

    21 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Hypersonic Airbreathing Missile

    Hunt, J. L. / Lawing, P. L. / Marcum, D. C., Jr. | NTRS | 1978



    Hypersonic airbreathing propulsion

    Avery, W.H. / Dugger, G.L. | Engineering Index Backfile | 1964


    Hypersonic airbreathing missile concepts under study at NASA LangleyResearch Center

    HUNT, J. / JOHNSTON, P. / CUBBAGE, J. et al. | AIAA | 1982


    Aerodynamic and inlet flow characteristics of several hypersonic airbreathing missile concepts

    Dillon, J. L. / Marcum, D. C., Jr. / Johnston, P. J. et al. | NTRS | 1980