| 单翼大挠性航天器全局模态动力学建模及试验 |
| |
| 引用本文： | 袁秋帆,王超磊,齐乃明,曹世磊.单翼大挠性航天器全局模态动力学建模及试验[J].宇航学报,2019,40(4):369-377. |
| |
| 作者姓名： | 袁秋帆 王超磊 齐乃明 曹世磊 |
| |
| 作者单位： | 1. 上海宇航系统工程研究所，上海 201109；2. 北京仿真中心航天系统仿真重点实验室，北京 100854；
3. 哈尔滨工业大学航天工程系，哈尔滨 150001 |
| |
| 基金项目： | 国家自然科学基金（11672093）；国家自然科学基金（U1737207）；航天科技集团-哈尔滨工业大学联合技术创新项目 |
| |
| 摘 要： | 针对小中心刚体-单侧大挠性结构构型的航天器，通过定义广义全局模态振型，提出一种全局模态动力学模型。采用统一形式描述整体刚体运动和整体挠性变形，基于哈密顿原理推导了全局模态动力学方程，结合瑞利瑞兹法推导了非约束模态频率和模态振型的计算方法。通过仿真和试验校验了全局模态动力学模型的准确性。与有限元模型对比，分析了非约束模态频率随着刚柔质量比和惯量比的变化情况，第一阶模态频率的最大误差为0.003 Hz，说明全局模态动力学模型能够比较准确地描述非约束模态频率；理论模型能够比较准确地描述动态响应，端部横向位移的最大误差为2.6%；基于气浮平台构建了试验系统，理论模型、有限元仿真和物理试验结果均比较接近，说明理论模型准确描述了非约束模态频率随刚柔耦合特性变化的规律。
|
| 关 键 词： | 全局模态动力学模型 全局模态振型 非约束模态频率 瑞利瑞兹法 |
| 收稿时间： | 2018-05-23 |
Global Dynamic Modeling for a Spacecraft with Single Large Flexible Structure and Experimental Study |
| |
| YUAN Qiu fan,WANG Chao lei,QI Nai ming,CAO Shi lei.Global Dynamic Modeling for a Spacecraft with Single Large Flexible Structure and Experimental Study[J].Journal of Astronautics,2019,40(4):369-377. |
| |
| Authors: | YUAN Qiu fan WANG Chao lei QI Nai ming CAO Shi lei |
| |
| Affiliation: | 1. Shanghai Aerospace System Engineering Institute, Shanghai 201109, China; 2. Science and Technology on Special System Simulation Laboratory, Beijing Simulation Center, Beijing, 100854，China; 3. School of Astronautics, Harbin Institute of Technology, Harbin 150001, China |
| |
| Abstract: | A global modal dynamic model is proposed for a spacecraft with a small center rigid body and a single large flexible structure. The global rigid body motion and the global flexible deformation are described in a unified form. Based on the Hamilton principle, the global modal dynamics equations are derived, and the calculation method of the unconstrained modal frequencies and modal shapes is derived by the Rayleigh-Ritz method. The accuracy of the global modal dynamics model is verified by the simulation and experiments. Compared with the finite element model, the variation of the unconstrained modal frequency along with the mass and the inertia ratios is analyzed. The results show that the global modal dynamic model describes the unconstrained modal frequency more accurately. The maximum error of the first modal frequency is 0.003 Hz. The dynamic response is accurately described with the maximum error of 2.6%. The experimental system is constructed, and the measured unconstrained modal frequencies are consistent with the theoretical analysis and the finite element simulation results. It shows that the theoretical model accurately describes the variation of the unconstrained modal frequency with the rigid-flexible coupling characteristics. |
| |
| Keywords: | Global modal dynamic model Global modal shapes Unconstrained modal frequencies Rayleigh-Ritz method |
| 本文献已被 CNKI 等数据库收录！ |
| 点击此处可从《宇航学报》浏览原始摘要信息 |
|
点击此处可从《宇航学报》下载全文 |
