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运用有限元手段建立三维复杂翼面结构的数值仿真模型,研究翼面结构的动力学固有特性,并通过原装支撑模态试验获得了翼面结构的前三阶模态参数,将理论计算与试验结果进行比对,验证了有限元模型计算的有效性。
The finite element method is used to establish the numerical simulation model of the three-dimensional complex airfoil structure. The inherent aerodynamic characteristics of the airfoil structure are studied. The first three modes of the airfoil structure are obtained through the original support modal test. The theoretical calculation and test The results are compared and verified the validity of the finite element model calculation.