典型阻尼结构正弦振动响应模型修正方法  

Sine Vibration Response Model Updating Method in Classic Damped Structure

作　　者：秦玉灵[1] 韩增尧[1] 邹元杰[1] 王建民[2] 

机构地区：[1]中国空间技术研究院,北京100094 [2]中国运载火箭技术研究院北京强度环境研究所,北京100076

出　　处：《中国空间科学技术》2014年第3期8-14,共7页Chinese Space Science and Technology

基　　金：973计划(613133)资助项目

摘　　要：直接基于正弦响应数据的模型修正研究较少,发展基于正弦振动试验数据的模型修正方法对航天工程实际中有限元建模水平的提高具有重要意义。基于正弦振动响应数据的模型修正关键在于修正后曲线特征频率及其响应幅值的一致性。文章对基础激励下结构响应分析方法进行了推导,在此基础上用两步修正方法实现了分析模型与试验模型特征频率和响应峰值的匹配,最后采用国际通用算例GARTEUR桁架模型对两步修正方法进行了验证。结果表明,经两步修正后分析模型基频与试验模型一致,且前10阶频率误差低于0.15%,典型节点响应峰值误差低于1%。The sine-vibration-data-based model updating method plays an important role in improving the finite element modeling level in spacecraft engineering.The key to sine-vibration-data-based model updating method is the coherence of the modal frequencies and the response curves of the model before ＆ after updated.Firstly,the analysis method of the structure response was derived based on the base excitation.Secondly,the updating method was studied in two steps,which makes the modal frequencies and the response curves of the analysis model consistent with that of the test model.Finally,the GARTURE truss model was used to validate the two step updating method.The results show that the fundamental frequencies of the analysis model agree with the test model,the first ten modal frequency error is under 0.15％,and the response peak error of the typical points is less than 1％.

关 键 词：正弦振动试验 模型修正 基础激励 特征频率 响应峰值 航天器结构 

分 类 号：TU317.1[建筑科学—结构工程]