航天器环境工程2018，Vol.35Issue(2)：128-134,7.DOI:10.3969/j.issn.1673-1379.2018.02.005
利用航天器分舱段振动试验数据获取整器响应的方法
The response of whole spacecraft structure obtained based on single-cabin vibration test data
摘要
Abstract
To meet the requirement for the vibration test for the coming ultra large spacecraft structures, single-cabin vibration tests have to be carried out for individual substructures. This paper proposes a method to obtain the transfer function of the whole spacecraft based on the substructure vibration test data. With the mapping relations among different boundary modal shapes, the modal shape of a certain cabin with fixed ends is identified. Then, the modal parameters of the combined structure are calculated by the modal integration technique, and the transfer functions of the acceleration response of the structure are calculated, so the test response curve for the whole spacecraft can be deduced under the given acceleration test conditions. The method is verified by a dynamics simulation, and its engineering feasibility is shown.关键词
航天器/分舱段振动试验/模态映射/加速度响应/传递函数Key words
spacecrafts/single-cabin vibration test/modal mapping/acceleration response/transfer function分类
航空航天引用本文复制引用
王泽宇,邹元杰,刘明辉,冯咬齐,刘绍奎,朱卫红..利用航天器分舱段振动试验数据获取整器响应的方法[J].航天器环境工程,2018,35(2):128-134,7.基金项目
装备发展部预先研究项目(编号:41410010301) （编号:41410010301）
