| 带弹性附件的卫星的姿态动力学方程 |
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| 引用本文： | 邵成勋,黄文虎.带弹性附件的卫星的姿态动力学方程[J].宇航学报,1989(2):79-85. |
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| 作者姓名： | 邵成勋 黄文虎 |
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| 作者单位： | 哈尔滨工业大学航天学院
(邵成勋，黄文虎，张嘉钟，赵美德)，哈尔滨工业大学航天学院(刘玉岚) |
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| 摘 要： | 本文采用虚功形式的d’A1embert原理建立了带弹性附件的卫星的姿态动力学方程。方程便于与有限元程序结合。对于非自旋卫星,可以给出线性化的方程。文中建议以各阶约束模态的角动量系数对弹性附件的惯矩的贡献作为降价的参考较为方便。文章给出了一个数字例。
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| 关 键 词： | 卫星 姿态控制 动力学方程 |
THE ATTITUDE DYNAMICS OF A SATELLITE WITH FLEXIBLE APPENDAGES |
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| Shao Chengxun Huang Wenhu Zhang Jiazhong Zhao Meide Liu Yulan.THE ATTITUDE DYNAMICS OF A SATELLITE WITH FLEXIBLE APPENDAGES[J].Journal of Astronautics,1989(2):79-85. |
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| Authors: | Shao Chengxun Huang Wenhu Zhang Jiazhong Zhao Meide Liu Yulan |
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| Institution: | Harbin Institute of Technology |
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| Abstract: | The equations of attitude dynamics of a satellite with flexible appendages are derived in this paper by the use of the d'Alembert principle in virtual work form. It is suggested that the contributions of the modal angular momentum to the inertia moment of the appendage can be used as a criteria for the reduction of the orders of these equations. A numerical example is given in this paper. |
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| Keywords: | Attitude dynamics Satellite attitude control Flexible structure |
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