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提出了一件通过特征方程反问题识别翼面弹性支承边界参数的改进方法。新方法以动柔度矩阵特征方程为基础建立以边界内力为未知数的方程，由摸态叠加法对可测自由度上不完全的振型拟合获取不可测自由度上的振型，从而避免了自由度压缩，又能减少对计算机内存贮量的需求。数值仿真算例和工程实例表明，本文方法具有良好的识别精度和数值稳定性，具有更广泛的适应性和工程实用价值。
An improved method of identifying boundary parameters of the elastic support of the airfoil by inverse problem of eigenvalue equations is proposed. The new method builds the equation based on the dynamic flexibility matrix eigenvalue equation, which is based on the unknown internal force of the boundary. The modal superposition method is used to obtain the vibration modes on the unmeasured degrees of freedom from the incomplete vibration modes on the measured degrees of freedom, thus avoiding Freedom of compression, but also reduce the demand for computer memory. Numerical simulation examples and engineering examples show that the proposed method has good recognition accuracy and numerical stability, and has a wider range of adaptability and engineering practical value.