| 椭圆参考轨道的卫星编队队形保持控制设计 |
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| 引用本文： | 崔海英,李俊峰,高云峰. 椭圆参考轨道的卫星编队队形保持控制设计[J]. 工程力学, 2007, 24(4): 147-151 |
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| 作者姓名： | 崔海英 李俊峰 高云峰 |
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| 作者单位： | 清华大学航天航空系,北京100084;清华大学航天航空系,北京100084;清华大学航天航空系,北京100084 |
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| 基金项目： | 国家自然科学基金 , 高等学校博士学科点专项科研项目 |
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| 摘 要： | 以Lawden方程作为动力学模型,建立状态方程,利用线性二次型性能指标最优控制(LQR)对卫星编队队形进行保持控制。首先对近地轨道的主要摄动J2项摄动和大气阻力摄动进行描述,得到了影响编队队形的相对摄动的表达式。然后通过合理的选择控制加权矩阵R,用无约束的线性二次型优化方法解决了电推力火箭有控制约束的优化问题。仿真结果表明,这种控制方法是有效的。
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| 关 键 词： | 航天器飞行力学 卫星编队飞行 Lawden方程 队形保持 LQR 相对摄动 |
| 文章编号： | 1000-4750（2007）04-0147-05 |
| 修稿时间： | 2005-08-252006-04-25 |
CONTROL OF SATELLITE FORMATION KEEPING IN ECCENTRIC ORBITS |
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| CUI Hai-ying,LI Jun-feng,GAO Yun-feng. CONTROL OF SATELLITE FORMATION KEEPING IN ECCENTRIC ORBITS[J]. Engineering Mechanics, 2007, 24(4): 147-151 |
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| Authors: | CUI Hai-ying LI Jun-feng GAO Yun-feng |
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| Abstract: | The state equation based on the Lawden’s equations is established and control method for satellite formation keeping is investigated using Linear Quadratic Regulators (LQR). Firstly, the relative disturbing forces are expressed while considering the J 2 perturbation and atmospheric drag as two major disturbing forces in low earth orbit. Then, by choosing the control weighted matrix R reasonably, the constrained optimization problem as formation keeping with electric rocket propellant can be transformed into the unconstrained optimization to be solved. The simulations show that this control method is effective. |
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| Keywords: | spacecraft flying mechanics satellite formation flying Lawden’s equations formation keeping LQR relative disturbing force |
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