The invention discloses a helicopter tail rotor simulation system for a wind tunnel test. The system comprises a base, a driving mechanism, a supporting arm, a tilting adjustment mechanism and a tailrotor transmission measurement control module, wherein one end of the supporting arm is a fixed end, the other end is a tilting end, the fixed end of the supporting arm is rotatably connected with thebase, the driving mechanism is used for driving the supporting arm to rotate around the base, the tilting adjusting mechanism is installed at the tilting end of the supporting arm and can move in theaxial direction of the supporting arm and rotate around the axial direction of the supporting arm, and the tail rotor transmission measurement control module is rotatably connected with the tilting adjustment mechanism. Flight states of different helicopters at different inclination angles can be simulated.

    本发明公开了一种风洞试验用直升机尾桨模拟系统,其包括基座、驱动机构、支撑臂、倾转调节机构和尾桨传动测量操纵模块,支撑臂的一端为固定端,另一端为倾转端,支撑臂的固定端与基座转动连接,驱动机构用于驱动支撑臂绕基座转动,倾转调节机构安装在支撑臂的倾转端,倾转调节机构能够沿支撑臂的轴向移动以及绕支撑臂的轴向转动,尾桨传动测量操纵模块与倾转调节机构转动连接。本发明能够模拟不同直升机在不同倾角下的飞行状态。


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    Titel :

    Helicopter tail rotor simulation system for wind tunnel test


    Weitere Titelangaben:

    一种风洞试验用直升机尾桨模拟系统


    Beteiligte:
    HUANG ZHIYUAN (Autor:in) / YANG YONGDONG (Autor:in) / PENG XIANMIN (Autor:in) / ZHANG GUICHUAN (Autor:in) / TANG MIN (Autor:in) / ZHAO LIANGLIANG (Autor:in)

    Erscheinungsdatum :

    2020-08-28


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen



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