固体火箭自由运行状态截面弯矩识别方法

An Identification Method for Transverse Response Moment of Solid Rocket during Free Flight State

首先对固体火箭自由运行状态得到的低频振动数据进行两次积分得到位移参数,进而利用模态叠加原理求解各阶广义坐标,再根据模态弯矩来识别截面横向响应弯矩,给出了识别结果。识别结果与截面弯矩测量结果接近,说明本文提出的方法对自由运行状态的固体火箭截面横向载荷的评估及设计具有重要的参考意义。

The displacement of the solid rocket is obtained by the integration of the low-frequency vibration during free flight state. Then by the modal superimposition method,a method for identifying the transverse load of solid rocket is introduced. Based on an example of solid rocket remoting data,the results of transverse bending moments are given. Identified result and measured cross section bending moment are approximate,proving that such a method is practical in load identification for similar problems and much useful in engineering.