| 利用航天器分舱段振动试验数据获取整器响应的方法 |
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| 引用本文： | 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. |
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| 作者姓名： | 王泽宇 邹元杰 刘明辉 冯咬齐 刘绍奎 朱卫红 |
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| 作者单位： | 北京空间飞行器总体设计部, 北京 100094,北京空间飞行器总体设计部, 北京 100094,北京卫星环境工程研究所, 北京 100094,北京卫星环境工程研究所, 北京 100094,北京空间飞行器总体设计部, 北京 100094,北京空间飞行器总体设计部, 北京 100094 |
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| 基金项目： | 装备发展部预先研究项目（编号：41410010301） |
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| 摘 要： | 未来大型组合体航天器振动试验可能难以在现有设备上进行,需要进行分舱考核。文章针对此问题开展了利用分舱段振动试验获取整器响应的方法研究。提出的方法为:根据不同界面下模态的映射关系,利用单舱段的振动试验数据辨识出舱段的两端固支模态;采用模态综合技术计算出整器组合体模态参数,拟合出结构的加速度响应传递函数;结合整器的加速度试验条件可以给出整器的试验响应曲线。仿真验证结果表明该方法合理可行,具有工程应用价值。
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| 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 |
| 收稿时间： | 2017/10/23 0:00:00 |
| 修稿时间： | 2018/3/21 0:00:00 |
The response of whole spacecraft structure obtained based on single-cabin vibration test data |
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| WANG Zeyu,ZOU Yuanjie,LIU Minghui,FENG Yaoqi,LIU Shaokui and ZHU Weihong.The response of whole spacecraft structure obtained based on single-cabin vibration test data[J].Spacecraft Environment Engineering,2018,35(2):128-134. |
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| Authors: | WANG Zeyu ZOU Yuanjie LIU Minghui FENG Yaoqi LIU Shaokui and ZHU Weihong |
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| Institution: | Beijing Institute of Spacecraft System Engineering, Beijing 100094, China,Beijing Institute of Spacecraft System Engineering, Beijing 100094, China,Beijing Institute of Spacecraft Environment Engineering, Beijing 100094, China,Beijing Institute of Spacecraft Environment Engineering, Beijing 100094, China,Beijing Institute of Spacecraft System Engineering, Beijing 100094, China and Beijing Institute of Spacecraft System Engineering, Beijing 100094, China |
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| 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. |
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| Keywords: | spacecrafts single-cabin vibration test modal mapping acceleration response transfer function |
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