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首页> 外文期刊>Chinese journal of aeronautics >Rotor Vibratory Load Prediction Based on Generalized Forces
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Rotor Vibratory Load Prediction Based on Generalized Forces

机译：基于广义力的转子振动载荷预测

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Three rigid-body-motion DOFs are introduced for the motion of the flap, lag hinge and pitch bearing. The rotor blade is discretized using a five-nodes, 15 DOFs beam finite element. The dynamic coupling effect between the rigid motion of the blade and the nonlinear elastic deflections is taken into account. Utilizing the constitutive law of the curvilinear coordinate system, the typical moderate deflection beam theory is reformulated. In addition, the Leishman and Beddoes unsteady and dynamic stall model is incorporated and the inflow is evaluated with the free wake analysis. The derived nonlinear ordinary differential equations with time - dependent coefficients of the rotor blade are given in the sense of the generalized forces. The sectional loads of the blade and the equations of motion are solved simultaneously in the physical space. The blade vibratory loads predicted by present analysis show generally fair a-greement with the flight test data of the SA349/2 Gazelle helicopter.
机译：引入了三个刚体运动自由度，用于襟翼，滞后铰链和俯仰轴承的运动。转子叶片使用五节点，15 DOFs束有限元离散化。考虑了叶片的刚性运动与非线性弹性挠度之间的动态耦合效应。利用曲线坐标系的本构定律，重构了典型的中等偏转梁理论。此外，并入了Leishman和Beddoes的非稳态和动态失速模型，并利用自由尾流分析评估了流入量。在广义力的意义上，给出了导出的具有时间相关系数的转子叶片非线性常微分方程。叶片的截面载荷和运动方程在物理空间中同时求解。通过当前分析预测的叶片振动载荷与SA349 / 2瞪羚直升机的飞行测试数据总体上显示出合理的一致性。

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