| 引用本文: | 王杰,吴军,邹杰.挠性航天器变幅值输入成形姿态机动策略.[J].国防科技大学学报,2022,44(1):68-76.[点击复制] |
| WANG Jie,WU Jun,ZOU Jie.Flexible spacecraft attitude maneuver planning based on variable amplitudes input shaping method[J].Journal of National University of Defense Technology,2022,44(1):68-76[点击复制] |
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| 挠性航天器变幅值输入成形姿态机动策略 |
| 王杰,吴军,邹杰 |
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(国防科技大学 空天科学学院, 湖南 长沙 410073)
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| 摘要: |
| 针对变参数挠性航天器的姿态机动问题,在变幅值零振动成形器的基础上,提出了鲁棒性较强的变幅值零振动和零微分成形器设计方法,设计了鲁棒姿态机动策略。该机动策略的控制目标是,将航天器机动到期望状态的同时,消除挠性结构的残余振动。以含转动挠性太阳翼的航天器进行三轴姿态机动为例,进行数值仿真。仿真结果表明,该机动策略对挠性结构频率变化以及阻尼系数不确定性具有较强的鲁棒性。 |
| 关键词: 变参数挠性航天器 姿态机动 残余振动 变幅值输入成形 鲁棒性 |
| DOI：10.11887/j.cn.202201011 |
| 投稿日期：2020-07-05 |
| 基金项目:国家自然科学基金资助项目(11802335) |
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| Flexible spacecraft attitude maneuver planning based on variable amplitudes input shaping method |
| WANG Jie, WU Jun, ZOU Jie |
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(College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China)
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| Abstract: |
| In order to solve the attitude maneuver problem for flexible spacecraft with time-varying parameters, the variable amplitudes zero vibration derivative shaper with stronger robustness was developed based on the variable amplitudes zero vibration shaper. The robust attitude maneuver strategy, in which its objective was to maneuver the spacecraft to the desired attitude state and cancel the residual vibration of the rotating flexible appendages at the same time, was proposed. Simulations were conducted by means of a spacecraft with rotating solar wings which undergoes three-axis maneuvers. The results indicate that this strategy is robust to frequency variations, uncertainties of damping coefficient and other uncertain factors. |
| Keywords: flexible spacecraft with time-varying parameters attitude maneuver residual vibration variable amplitudes input shaping robustness |
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