The invention provides a novel helicopter blade dynamic load identification method based on blade profile measurement bending moment. And according to the stress condition of the blade unit, establishing an inverse transfer matrix of the blade, substituting the inverse transfer matrix into the actually measured bending moment of the blade, calculating to obtain the displacement response of the blade, establishing a kinetic model of the rotating blade, and calculating the inherent frequency and vibration mode of the blade. And calculating generalized coordinates of the blade according to the displacement response and the modal displacement of the blade, and finally substituting the generalized coordinates into an aerodynamic force identification equation derived from a blade coupling motion equation to calculate the aerodynamic load of the rotor blade.

    本发明提出一种基于桨叶剖面测量弯矩的直升机桨叶动载荷识别新方法。根据桨叶单元的受力情况,建立桨叶的逆传递矩阵,代入桨叶实测弯矩,计算得到桨叶位移响应,建立旋转桨叶的动力学模型,计算桨叶的固有频率和振型。根据桨叶的位移响应和模态位移计算桨叶的广义坐标,最后代入桨叶耦合运动方程推导的气动力识别方程即可计算旋翼桨叶的气动载荷。


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    Title :

    Helicopter blade dynamic load identification method based on blade profile measurement bending moment


    Additional title:

    基于桨叶剖面测量弯矩的直升机桨叶动载荷识别方法


    Contributors:
    SHANG LINA (author) / XIA PINQI (author) / QI YUSONG (author) / RUAN XUEMAN (author)

    Publication date :

    2022-11-15


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    G01M TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES , Prüfen der statischen oder dynamischen Massenverteilung rotierender Teile von Maschinen oder Konstruktionen / 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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