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基于有限元理论及自由尾迹方法,建立了一套适用于各向异性复合材料无铰式旋翼的气弹稳定性分析方法.为了模拟复合材料旋翼气弹特性,截面特性参数采用二维线性有限元方法分析得到,展向一维梁则采用考虑剪切变形的23自由度非线性梁单元模拟,并将自由尾迹分析模型用于计算旋翼非均匀诱导速度场,基于升力线模型构建了一个高效且较为精细的气动分析模块.在此基础上开展了无铰式旋翼气弹稳定性分析,算例计算及验证表明建立的模型能有效地用于复合材料旋翼非定常气动载荷预估及进行气弹稳定性分析.最后细致分析并获得了复合材料铺层角对无铰式旋翼气弹稳定性参数的影响规律,结果表明:算例在小拉力系数(0.0025)下,截面竖直铺层角在10°到25°会发生气弹稳定性问题,这在真实型号设计中应当注意避免.
Based on the finite element theory and the free wake method, a set of aeroelastic stability analysis method is developed for anisotropic rotor with anisotropic composite materials. In order to simulate the aeroelastic properties of the composite rotor, the cross-section parameters are determined by two-dimensional linear finite element method By using the method, the 23-degree-of-freedom nonlinear beam element considering the shear deformation is used to simulate the one-dimensional beam, and the free-wake analysis model is used to calculate the rotor non-uniform induced velocity field. Based on the lift-line model, More sophisticated aerodynamic analysis module.Analytical stability analysis of the hingeless rotor aeroelastic is carried out.The calculation and verification of the example show that the model can be effectively used to predict the unsteady aerodynamic loads of the composite rotor and to perform the gas bomb Stability analysis.Finally, the effect of composite lay-up angle on the parameters of the aero-elastic bouncing of the hingeless rotor was analyzed in detail. The results show that under the low coefficient of pull (0.0025), the vertical lay angle Aeroelastic stability problems occur at 10 ° to 25 °, which should be avoided in real-world designs.