吉林大学学报(工学版)

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基于最优状态反馈的小推力转移轨道制导策略

尚海滨1,崔平远1,栾恩杰2   

  1. 1.哈尔滨工业大学 深空探测基础研究中心,哈尔滨 150080; 2.国防科学技术工业委员会 月球探测工程中心,北京 100000
  • 收稿日期:2006-08-28 修回日期:2006-10-21 出版日期:2007-07-01 发布日期:2007-07-01
  • 通讯作者: 崔平远

Guidance strategy for lowthrust transfer trajectories based on optimal states feedback technology

Shang Hai-bin1,Cui Ping-yuan1,Luan En-jie2   

  1. 1.Deep Space Exploration Research Center, Harbin Institute of Technology, Harbin 150080,China; 2.Commission of Science Technology and Industry for National Defence, Lunar Exploration Engineering Center, Beijing 100000, China
  • Received:2006-08-28 Revised:2006-10-21 Online:2007-07-01 Published:2007-07-01
  • Contact: Cui Ping-yuan

摘要: 针对小推力变轨技术研究中的难点之一——飞行器的制导问题,提出了一种基于最优状态反馈的自主制导策略。首先利用传统Gauss型运动方程,推导出三个轨道根数增大最快的独立控制律;然后根据当前根数与目标值的偏差量对独立控制律进行加权组合;最后为高效可靠地获得最优制导律,采用一种遗传算法和逐次二次规划相结合的混合方法对权重进行了优化。该制导算法设计简单,无须预存参考轨道,能够实现飞行器的自主制导,并且具有燃料消耗次优的特点。仿真计算验证了该算法的有效性。

关键词: 航天器制导与控制, 小推力, 自主制导, 独立控制律, 混合方法, 轨道转移

Abstract: The guidance algorithm for spacecraft is one of the difficult techniques in lowthrust transfer research. In this paper, we have presented an autonomous guidance strategy based on optimal states feedback technology. First, by utilizing classical Gauss motion equations, we derived the three separate control laws, which could maximize the time rate of change of a desired orbital element. Then, the separate control laws were blended based on the deficit between current and target value of orbital state. Finally, to obtain the optimal guidance law effectively and reliably, a hybrid method combining genetic algorithm with sequential quadratic programming was used to optimize the weight values. The guidance law design is simple, without relying on a stored reference trajectory, and could be used for spacecraft's autonomous guidance. Furthermore, it has the characteristic of near optimal-fuel. The effectiveness of the guidance algorithm has been validated by numerical simulation.

Key words: spacecraft navigation and control, lowthrust, autonomous guidance, separate control law, hybrid method, orbit transfer

中图分类号: 

  • V448.2
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