太阳帆航天器悬浮轨道动力学与控制

钱航; 郑建华; 于锡峥; 高东

doi:10.11728/cjss2013.04.458

太阳帆航天器悬浮轨道动力学与控制

doi: 10.11728/cjss2013.04.458

钱航^1,2,3,
郑建华¹,
于锡峥^1,2,
高东¹

1.
中国科学院空间科学与应用研究中心北京 100190
2.
航天飞行动力学技术重点实验室北京 100094
3.
中国科学院大学北京 100190

基金项目: 中国科学院战略性先导科技专项资金(XDA04060303);航天飞行动力学技术重点实验室开放基金项目(2012afdl028)和太阳帆民用航天项目共同资助

详细信息

作者简介:
钱航, qianhang10@mails.ucas.ac.cn

中图分类号: V416
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- 被引次数: 0
出版历程
- 收稿日期: 2012-09-21
- 修回日期: 2013-03-08
- 刊出日期: 2013-07-15

Dynamics and Control of Displaced Orbits for Solar Sail Spacecraft

1.
Center for Space Science and Applied Research, Chinese Academy of Sciences, Beijing 100190
2.
Science and Technology on Aerospace Flight Dynamics Laboratory, Beijing 100094
3.
University of Chinese Academy of Sciences, Beijing 100190

摘要

摘要: 基于线性动力学模型和非线性动力学模型,研究了太阳帆航天器日心悬浮轨道保持与控制问题.首先,推导出了柱坐标形式的太阳帆动力学方程,并在参考悬浮轨道附近线性化以建立状态方程,然后对状态方程进行可控性分析.通过合理选择控制变量加权矩阵R,用线性二次型调节器(LQR)对线性模型进行控制.将得到的控制律代入非线性模型中进行验证,表明该控制律渐近稳定,并且具有良好的控制精度,可实现太阳帆悬浮轨道控制.
- 太阳帆 /
- 悬浮轨道 /
- 可控性 /
- 线性二次型调节器
Abstract: Based on the linear dynamics model and nonlinear dynamics model, the sun-centred displaced orbits keeping control problem is studied. Firstly, the solar sail dynamics model in cylindrical coordinate form is derived and orbit controllability of the state equation by linearizing the model along the nominal orbit is investigated. Then, by choosing the control weighted matrix R reasonably, a control law for the linear model is designed using the Linear-Quadratic Regulation (LQR) approach. The numerical simulations which are obtained by taking the control law into the nonlinear model indicate that the designed controller which has asymptotic stability and high control accuracy is capable.
- Solar sail /
- Displaced orbit /
- Controllability /
- Linear-quadratic regulation

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参考文献(8)

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