| 挠性卫星轨控期间动力学与姿态控制 |
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| 引用本文： | 刘莹莹,周军.挠性卫星轨控期间动力学与姿态控制[J].空间控制技术与应用,2008,34(2):9-13. |
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| 作者姓名： | 刘莹莹 周军 |
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| 作者单位： | 西北工业大学精确制导与控制研究所,西安,710072 |
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| 基金项目： | 民用航天计划(C5120062702); 航天支撑基金(2007CH020004)资助项目 |
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| 摘 要： | 卫星轨道控制期间，轨道控制推力会激振挠性太阳帆板，从而也影响卫星的姿态。用拉格朗日方程建立了带有大型太阳帆板的卫星动力学模型，分析了卫星质心运动、姿态运动与挠性振动的耦合关系。根据姿态控制推力器的输出特性，设计了轨道控制期间卫星姿态控制方案。通过数学仿真验证了轨道控制推力对挠性帆板与卫星姿态的影响，验证了轨控期间姿态控制方案的有效性。
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| 关 键 词： | 挠性卫星 轨道机动 姿态控制 挠性振动 |
Dynamics and Attitude Control of Flexible Satellite during Orbital Maneuver |
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| LIU Yingying,ZHOU Jun.Dynamics and Attitude Control of Flexible Satellite during Orbital Maneuver[J].Aerospace Contrd and Application,2008,34(2):9-13. |
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| Authors: | LIU Yingying ZHOU Jun |
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| Abstract: | When the satellite takes orbital maneuver,the control force may stimulate the vibration of the flexible appendages and,therefore,affects the attitude of the satellite.The dynamic model of the satellite with a large solar panel is established via Lagrange equations.The coupling relations between the motion of the satellite orbit,the attitude and the flexible vibration are analyzed.The attitude control law is designed for the orbital maneuver with considering the output character of the attitude control thrus... |
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| Keywords: | flexible satellite orbital maneuver attitude control flexible vibration |
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