The invention discloses a supersonic-speed or hypersonic-speed aircraft safety protection method based on flow control, and the method comprises the steps: adjusting the frequency and range of low-frequency pressure pulsation of a flow field discontinuous surface interference region caused by the unsteady motion of a flow field discontinuous surface based on the excitation of an unsteady high-repetition-frequency pulse flow field; strong coupling between pressure pulsation of a low-frequency interference area of a flow field discontinuity surface and an aircraft surface structure is avoided, and the aircraft surface structure is complete and reliable. The method is applied to the technical field of supersonic or hypersonic aircrafts, the safety protection capability of the aircraft can be effectively improved by applying unsteady high repetition frequency pulse flow field excitation to the flow field discontinuous surface interference area of the supersonic or hypersonic aircraft, and the safety protection capability of the aircraft can be effectively improved by controlling the unsteady motion of the flow field discontinuous surface and locking the flow field discontinuous surface at a specific frequency. The range of low-frequency pressure pulsation in an interference area can be effectively reduced, so that vibration of the surface structure of the aircraft is reduced, and safety protection of the supersonic or hypersonic aircraft is achieved.

    本发明公开了一种基于流动控制的超声速或高超声速飞行器安全防护方法,基于非定常高重频脉冲流场激励,调节流场间断面非定常运动引发的流场间断面干扰区低频压力脉动的频率和范围,避免流场间断面低频干扰区压力脉动与飞行器表面结构发生强耦合,保证飞行器表面结构完整可靠。本发明应用于超声速或高超声速飞行器技术领域,通过对超声速或高超声速飞行器的流场间断面干扰区施加非定常高重频脉冲流场激励,能够有效提升飞行器的安全防护能力,通过控制流场间断面的非定常运动,并锁定在特定频率,可以有效地减小干扰区低频压力脉动的范围,从而减少飞行器表面结构的振动,实现超声速或高超声速飞行器安全防护。


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Supersonic-velocity or hypersonic-velocity aircraft safety protection method based on flow control


    Weitere Titelangaben:

    基于流动控制的超声速或高超声速飞行器安全防护方法


    Beteiligte:
    ZHOU YAN (Autor:in) / LUO ZHENBING (Autor:in) / DENG XIONG (Autor:in) / ZHU YINXIN (Autor:in) / PENG WENQIANG (Autor:in) / XIE WEI (Autor:in) / LIU QIANG (Autor:in) / GAO TIANXIANG (Autor:in) / WANG YUNAN (Autor:in)

    Erscheinungsdatum :

    2024-01-05


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



    Supersonic-velocity hypersonic-velocity gas inlet duct adopting pneumatic unstart control method

    TAN HUIJUN / ZHANG QIFAN / CHEN HAO et al. | Europäisches Patentamt | 2015

    Freier Zugriff

    Hypersonic flow velocity measurements using laser velocimeter

    WANG, J. / ASHER, J. / MURRAY, D. | AIAA | 1973


    Method for designing double-air-inlet hypersonic-velocity wave-rider aircraft

    LI YIQING / YOU YANCHENG / TENG JIAN et al. | Europäisches Patentamt | 2015

    Freier Zugriff


    Prediction of inviscid supersonic/hypersonic aircraft flowfields

    VERHOFF, A. / STOOKESBERRY, D. | AIAA | 1992