The invention provides a coaxial dual-rotor transient pitch prediction method. The method comprises the following steps: establishing a finite element model of a blade unit; deducing a kinetic equation of a rotor and fuselage coupling system according to the finite element model of the blade unit; using a free wake model to calculate the induced velocity of each position of the blade; according to the induced speed of each position of the blade, calculating the aerodynamic load of the blade; substituting the aerodynamic load of the blade into a kinetic equation of the rotor and fuselage coupling system, and calculating to obtain a transient response of the blade; and converting the blade transient response into a blade tip spacing.

    本申请提供了一种共轴双旋翼瞬态桨尖间距预测方法,所述方法包括:建立桨叶单元的有限元模型;根据所述桨叶单元的有限元模型,推导旋翼与机身耦合系统的动力学方程;使用自由尾迹模型,计算得到桨叶各个位置的诱导速度;根据所述桨叶各个位置的诱导速度,计算得到桨叶的气动载荷;将所述桨叶的气动载荷代入所述旋翼与机身耦合系统的动力学方程,计算得到桨叶瞬态响应;将所述桨叶瞬态响应转换为桨尖间距。


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    Titel :

    Coaxial dual-rotor transient pitch prediction method


    Weitere Titelangaben:

    一种共轴双旋翼瞬态桨尖间距预测方法


    Beteiligte:
    FAN FENG (Autor:in) / ZHAO JINRUI (Autor:in) / YU ZHIHAO (Autor:in) / HUANG SHUILIN (Autor:in) / HUANG JIAN (Autor:in) / CHENG YI (Autor:in) / HE ZIHAO (Autor:in) / JIANG QIHUANG (Autor:in) / ZHANG SHIMING (Autor:in) / DUAN JINFAN (Autor:in)

    Erscheinungsdatum :

    07.03.2025


    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 / G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung



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