| 航天器微振动工装动力学特性仿真分析与试验验证 |
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| 引用本文： | 高海洋, 王栋, 李栋, 等. 航天器微振动工装动力学特性仿真分析与试验验证[J]. 航天器环境工程, 2019, 36(3): 252-256doi:10.12126/see.2019.03.009 |
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| 作者姓名： | 高海洋 王栋 李栋 刘明辉 韩晓健 樊世超 |
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| 作者单位： | 北京卫星环境工程研究所，北京 100094 |
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| 摘 要： | 微振动试验中为了模拟航天器的在轨自由边界，需要建立具备大承载低刚度的试验工装。文章提出一种简化的航天器与微振动工装组合体模型，引入考虑初始变形的模态分析理论对组合体模态频率特性进行仿真分析，并将某型号卫星微振动试验工装设计指标与试验测试指标进行对比。结果表明：用简化后的组合体模型计算得到的准刚体模态频率与实测值相近，简化模型提供的第六阶频率计算误差仅为0.3%，从而验证了分析模型与校核方法的有效性。
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| 关 键 词： | 航天器 微振动试验 工装设计 仿真分析 试验验证 |
| 收稿时间： | 2018-11-17 |
| 修稿时间： | 2019-05-24 |
Simulation and experimental verification of dynamic characteristics of spacecraft micro-vibration test fixture |
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| GAO H Y, WANG D, LI D, et al. Simulation and experimental verification of dynamic characteristics of spacecraft micro-vibration test fixture[J]. Spacecraft Environment Engineering, 2019, 36(3): 252-256doi:10.12126/see.2019.03.009 |
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| Authors: | GAO Haiyang WANG Dong LI Dong LIU Minghui HAN Xiaojian FAN Shichao |
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| Affiliation: | Beijing Institute of Spacecraft Environment Engineering, Beijing 100094, China |
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| Abstract: | To simulate a spacecraft on orbit with a free boundary, a micro-vibration test fixture with a large bearing capacity and a low stiffness should be established for the micro-vibration test. A simplified combination model for analyzing the micro-vibration fixture is presented in this paper. The modal analysis with consideration of the initial deformation is made to obtain the frequency characteristics of the assembly. The testing result of a typical satellite micro-vibration test fixture is used for comparison. The comparison between the analysis model and the testing results shows a 0.3% error for the sixth order frequency evaluation. |
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| Keywords: | spacecraft micro-vibration test fixture design simulation analysis test verification |
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