| 持续推进地球轨道转移的直接优化方法(英文) |
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| 引用本文： | 高扬,李卫琪.持续推进地球轨道转移的直接优化方法(英文)[J].中国航空学报,2009,22(1):56-69. |
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| 作者姓名： | 高扬 李卫琪 |
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| 作者单位： | Gao Yang(Academy of Opto-Electronics, Chinese Academy of Sciences, Beijing 100080, China);Li Weiqi(School of Automation Science and Electrical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China) |
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| 基金项目： | National Natural Science Foundation of China (10603005);;Foundation of President of the Academy of Opto-Electro-nics ( AOE-CX-200601) |
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| 摘 要： | 对于一大类时间最省(单次推进)和燃料最省(多次推进)的中等推力水平持续推进地球轨道转移问题,本文给出了一种系统的直接优化方法。首先,对于具有倾角和偏心率的目标轨道,我们介绍了一种惯性坐标转换方法得到更具一般性的末端约束条件。这个转换避免了逆行赤道轨道对春分点轨道根数引起的奇异,同时也提高了求解优化问题的收敛性。多次打靶法在本文中也得到了应用,给出了针对不同形式的轨道转移如何分配多次打靶变量的方法。基于惯性坐标转换和多次打靶法,最优控制问题转换为利用非线性规划法求解的参数优化问题。本文给出了单次推进时间最省以及多达12次推进燃料最省的轨道转移仿真结果,所有收敛结果均以简单定义的初值迭代得到。最后,我们讨论了利用模型预测控制进行自主制导的潜在方案。
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| 收稿时间： | 21 March 2008 |
Systematic Direct Approach for Optimizing Continuous-thrust Earth-orbit Transfers |
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| Gao Yang a,Li Weiqi b a Academy of Opto-Electronics,Chinese Academy of Sciences,Beijing ,China b School of Automation Science , Electrical Engineering,Beijing University of Aeronautics , Astronautics,Beijing ,China.Systematic Direct Approach for Optimizing Continuous-thrust Earth-orbit Transfers[J].Chinese Journal of Aeronautics,2009,22(1):56-69. |
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| Authors: | Gao Yang a Li Weiqi b a Academy of Opto-Electronics Chinese Academy of Sciences Beijing China b School of Automation Science Electrical Engineering Beijing University of Aeronautics Astronautics Beijing China |
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| Institution: | Gao Yang a,Li Weiqi b a Academy of Opto-Electronics,Chinese Academy of Sciences,Beijing 100080,China b School of Automation Science , Electrical Engineering,Beijing University of Aeronautics , Astronautics,Beijing 100191,China |
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| Abstract: | This article presents a systematic direct approach to carry out effective optimization of a wide range of continuous-thrust Earth-orbit transfers with intermediate-level thrust acceleration,including minimum-time (with a single burn arc) and mini-mum-fuel (with multiple burn arcs) transfers. With direct control parameterization,in which the control steering programs of burn arcs are interpolated through a finite number of nodes,the optimal control problem is converted into the parameter optimi-zation proble... |
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| Keywords: | low-thrust orbital transfer optimization multiple shooting variable specific impulse guidance scheme model predictive control |
| 本文献已被 CNKI 万方数据 ScienceDirect 等数据库收录！ |
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