The invention discloses a combined pneumatic control method for an aerodynamic rudder/reaction control system of a hypersonic flight vehicle, and belongs to the field of hypersonic flight vehicle design. As for the hypersonic flight vehicle which has a flat lifting body structure with a flat lower surface and a smaller side edge radius and has a sharp leading edge and a large sweepback body, a pair of expanding type body wing flaps is arranged on the windward side of the lower surface of the rear edge. With adoption of the combined pneumatic control method provided by the invention, reaction control system nozzles are arranged in front of the body wing flaps, pitching control of the flight vehicle is realized through deflection and jet of the body wing flaps, and rolling control of the flight vehicle is realized through differential motion and jet of the body wing flaps; the reaction control system nozzles are arranged on the side edge of the flight vehicle, and yaw control of the light vehicle is realized through jet. Through beneficialinterference of jet flow to the peripheral flow field of the aerodynamic rudder, the comprehensive control efficiency and the response speed of the aerodynamic rudder/reaction control system are increased, and the aerodynamic performance of the flight vehicle is improved. The control method has the characteristics of wide flight application range, high control efficiency and good economy.


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    Titel :

    Combined pneumatic control method for aerodynamic rudder/reaction control system of hypersonic flight vehicle


    Beteiligte:
    JIANG CHONGWEN (Autor:in) / LI CHUNXUAN (Autor:in) / GAO ZHENXUN (Autor:in) / XU CHENHAO (Autor:in) / DU PENG (Autor:in)

    Erscheinungsdatum :

    2015-04-01


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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