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。
Coaxial dual-rotor transient pitch prediction method
一种共轴双旋翼瞬态桨尖间距预测方法
07.03.2025
Patent
Elektronische Ressource
Chinesisch
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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