| 引用本文: | 刘新建,雷勇军,唐乾刚.大挠性太阳能帆板航天器的姿态控制.[J].国防科技大学学报,2003,25(5):6-8.[点击复制] |
| LIU Xinjian,LEI Yongjun,TANG Qiangang.The Attitude Control of Spacecraft with Large Flexible Solar Array[J].Journal of National University of Defense Technology,2003,25(5):6-8[点击复制] |
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| 大挠性太阳能帆板航天器的姿态控制 |
| 刘新建, 雷勇军, 唐乾刚 |
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(国防科技大学 航天与材料工程学院，湖南 长沙 410073)
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| 摘要: |
| 提出了一种简单有效的抑制太阳能帆板变形振动的PDA控制方法。其特点主要是在航天工程中常用PD方法的基础上，增加了航天器的刚性姿态加速度反馈，该方法经数值仿真和不同的实验系统证明，对大挠性航天器在姿态机动和位置保持控制时是一种简单可行的振动抑制策略，在大挠性航天器变轨和交会对接工程中具有参考价值。 |
| 关键词: 大挠性航天器 姿态控制 振动抑制 |
| DOI： |
| 投稿日期：2003-06-08 |
| 基金项目:国家863高技术资助项目(863-2) |
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| The Attitude Control of Spacecraft with Large Flexible Solar Array |
| LIU Xinjian, LEI Yongjun, TANG Qiangang |
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(College of Aerospace and Materials Engineering, National Univ. of Defense Technology, Changsha 410073, China)
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| Abstract: |
| A simple and efficient method PDA is put forward, which can suppress deformation vibration of the solar battery array. The attitude rigid acceleration feedback is combined with the classic PD method used usually in the aerospace engineering. The method has been demonstrated to be efficient in suppression of vibration for the attitude maneuver and keeping by virtue of numerical simulation and experiment. Certain applications may be made to the rendezvous and dock engineering or orbital maneuvour . |
| Keywords: flexible spacecraft attitude control vibration suppression |
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