火箭模态振型斜率预示方法研究

The Method in Indicating Mode Slope of the Launch Vehicle

通过对火箭惯性器件安装舱段的试验,完成了舱段的精细化建模及修正,通过对比舱段模态的模态振型斜率仿真与试验测量结果,推算出全箭模态振型斜率的仿真与试验结果偏差,并用全箭试验的一阶模态测量结果进行了验证,最终得到通过舱段试验进行惯性器件振型斜率预示和位置选择的方法。

In order to forecast the mode slope of the launch vehicle, the section which the inertial device installed is tested. Using the modal test data of the section on ground, a detailed section FEM model is built and updated. Then the section model is assembled in the entire launch vehicle model, the mode slope of the section in the particle test and the entire test is compared. In the end, a method using the section modal testing on ground to indicate the mode slope of the entire launch vehicle is summarized.