采用伪速度冲击响应谱评估蜂窝夹层板破坏边界

Damage Boundary Evaluation for Honeycomb Sandwich Panel Using Pseudo-Velocity Shock Response Spectrum

采用伪速度冲击响应谱(PVSRS)对航天器蜂窝夹层结构进行了冲击破坏边界评估。目前航天领域常用的冲击响应谱(SRS)是绝对加速度谱(AASRS),相较于绝对加速度谱,伪速度谱能更清楚地显示出结构在低频、中频和高频段不同的冲击响应特征。分析了弹性力和惯性力在低频、中频和高频段对结构安全性的影响,据此在对数四坐标伪速度谱上给出了相应的结构破坏边界。以一典型蜂窝夹层结构为研究对象,通过有限元分析计算得到的结构破坏边界与伪速度谱给出的结构破坏边界符合得较好。在航天器结构冲击安全性研究领域,本文采用的伪速度谱结构冲击破坏边界是对目前常用的加速度谱方法的一个有益补充。

This paper adopts the pseudo velocity shock response spectrum(PVSRS) to evaluate the damage boundary of spacecraft honeycomb sandwich structure. The shock response spectrum(SRS) commonly used in the aerospace field is the absolute-acceleration SRS(AASRS). Compared with the AASRS, the PVSRS more clearly shows the structure response under the shock load in low frequency, intermediate frequency and high frequency respectively. The effects of elastic force and inertial force on structural safety in low frequency, intermediate frequency and high frequency are analyzed. Based on the above discussions, the structure damage boundary is given in the logarithmic four-coordinate pseudo-velocity spectrum. The damage boundaries of a typical honeycomb sandwich structure are calculated by the finite element method and by the presented PVSRS method respectively, showing that these two boundaries agree well. The presented damage boundary analysis method based on PVSRS is a useful supplement to the commonly used AASRS method.