翼面弹性支承边界参数识别方法的改进

提出了一种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，由模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的振型，从而避免了压缩，又能减少对计算机内存贮量的需求。

AH IMPROVEMEHT ON BOUNOARY PARAMETER IOENTIFICATIOH OF ELASTICAL SUPPORT FOR MISSILE WING

in this paper, an improvable method is proposed xvhich identify the elastic support boundary parameter of missile wing by invcrersequestion of characteristic equation. The flew method founds an equationwhich taLes the internal force on the boulldary as unkllown number basingon characteristic equation of dynamic flexibility matrix. The modal shapeon the degree of freedom which can't be measured is gotten by fitting theincomplete modal shape on measured degree of freedom making use of modalsuperposition. So the .degree of freedom condensing is avoided and reducingthe requirement of computer's memory. The digital simulation example andpractical engineering example indicate the method in this paper has good identification precision and number stability. It has more extensi ye adaptability and practical value in engineering.