| 航天器附件展开动力学仿真 |
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| 引用本文： | 陈统,徐世杰.航天器附件展开动力学仿真[J].航天控制,2005,23(1):79-83. |
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| 作者姓名： | 陈统 徐世杰 |
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| 作者单位： | 北京航空航天大学,北京,100083;北京航空航天大学,北京,100083 |
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| 基金项目： | 国家自然科学基金资助项目(批准号:10172012) |
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| 摘 要： | 用Newton-Euler法建立了中心刚体带挠性附件的航天器动力学方程, 进行挠性附件展开的动力学仿真,研究附件展开对主体姿态的影响。当航天器 附件展开机构失效时,利用航天器姿态抖动来帮助展开附件。本文用ADAMS软 件建立了航天器的虚拟物理模型,用ADAMS和Matlab/Simulink联合仿真了航 天器姿态抖动过程。仿真结果表明此方法是有效的。
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| 关 键 词： | 航天器 挠性附件 多体动力学 Newton-Euler法 姿态抖动 ADAMS |
| 文章编号： | 1006-3242(2005)01-0079-05 |
| 修稿时间： | 2004年9月24日 |
Dynamic Simulation of Spacecraft Appendages Deploying |
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| Chen Tong,Xu Shijie.Dynamic Simulation of Spacecraft Appendages Deploying[J].Aerospace Control,2005,23(1):79-83. |
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| Authors: | Chen Tong Xu Shijie |
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| Institution: | Chen Tong Xu Shijie Beijing University of Aeronautics and Astronautics,Beijing 100083 |
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| Abstract: | The attitude motion equations of spacecraft composed of a main rigid body and flexible appendages are presented using Newton-Euler formulation. By dynamic simulation, the influence of deploying flexible appendages on the attitude of main body is studied. When the deployment drive mechanism is invalid, appendages are deployed passively using the attitude wobble of the main body. In this paper, the virtual multi-body physical model of the spacecraft is built in ADAMS circumstance.ADAMS links with Matlab/Simulink to simulate the attitude wobble process. The simulation results confirm that this method is feasible. |
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| Keywords: | Spacecraft Flexible appendages Multi-body dynamics Newton-Euler formulation Attitude wobble ADAMS |
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