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本文应用综合离散法对直升机桨叶进行动力分析,给出桨叶节点位移模式的表达式,对某桨叶计算了挥舞面弯曲振动、旋转面弯曲振动及耦合振动的固有频率,分析了桨叶在挥舞面的稳态响应。数值结果与实验数据及有限元法的计算结果非常一致。
In this paper, the dynamic analysis of the helicopter blades is carried out by the method of generalized discretization. The expression of the displacement mode of the blade joints is given. The natural frequency of the bending vibration, the bending vibration of the rotating plane and the coupled vibration of a blade is calculated. Steady response at the waving surface. Numerical results and experimental data and finite element method of the calculation results are very consistent.