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介绍用迭代方法求解直升机桨叶气动载荷中的非线性强迫振动方程。计算时，先假定诱导下洗已确定，求出桨叶的初始载荷；再通过非线性强迫振动方程求出弯－弯－扭弹性变形。以某一直升机为例，求出了桨叶的各阶谐波载荷和弹性变形。计算结果与实验数据吻合。
The iterative method is introduced to solve the nonlinear forced vibration equation in the aerodynamic loads of helicopter blades. The calculation is based on the assumption that the induced underwash has been determined and the initial load of the blade is obtained. Then, the elastic-plastic deformation of the bend-bend-torsion is obtained by the nonlinear forced vibration equation. Taking a certain helicopter as an example, the harmonic loads and elastic deformations of all the blades are obtained. The calculated results are in good agreement with the experimental data.