The purpose of this paper is to report recent results of an in-house conceptual study to evaluate the performance potential and research needs of airbreathing hypersonic missiles. An alkylated-borane (noncryogenic) fueled, dual-mode, ramjet/scramjet propulsion system structured with a Rene 41 inlet and a carbon-carbon combustor was assumed along with a Lockalloy heat sink fuselage structure and beryllium wings and control surfaces. Performance for an air-launched baseline missile with a 961 pound staging weight containing a 100 pound payload indicated excellent long range cruise, moderate acceleration and high maneuverability potential. A sizing study indicates that Mach 6 cruise ranges of the order of 2500 nautical miles for payloads of 300 pounds can be achieved with moderate size missile carry weights (9000 lbs.). Aerodynamic heating analyses indicate that unprotected heat-sink structures with internal insulation are feasible for ranges of several hundred miles. For ranges of several thousands of miles a multiwall radiation shield (Inconel/titanium) was selected for protection of the internally insulated heat sink structure.


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    Title :

    Conceptual study of hypersonic airbreathing missiles


    Contributors:

    Conference:

    Aerospace Sciences Meeting ; 1978 ; Huntsville, AL


    Publication date :

    1978-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Conceptual study of hypersonic airbreathing missiles

    HUNT, J. / LAWING, P. / MARCUM, D. et al. | AIAA | 1978




    Hypersonic airbreathing propulsion

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


    Hypersonic Airbreathing Missile

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