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论文:2013,Vol:31,Issue(5):701-705 |
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引用本文： |
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淡雪, 岳晓奎. 基于自适应积分的太阳同步轨道发射优化设计[J]. 西北工业大学 |
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Dan Xue, Yue Xiaokui. Optimization of Launch Trajectory for SSO (Sun Synchronous Orbit) Based on Adaptive Transfer Orbit[J]. Northwestern polytechnical university |
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| 基于自适应积分的太阳同步轨道发射优化设计 |
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| 淡雪1,2, 岳晓奎1,2 |
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1. 西北工业大学 航天学院, 陕西 西安 710072;
2. 航天飞行动力学技术重点实验室, 陕西 西安 710072 |
| 摘要: |
| 太阳同步轨道(Sun Synchronous Orbit,SSO)发射轨道的优化设计问题是一个具有严格内点约束和终端约束、终端时刻不确定型的最优控制问题,采用最优控制理论求解难度较大。针对此问题,首先将其转化为多重参数优化问题,然后提出一种自适应积分方法,根据高度和速度入轨条件自动确定中间转移轨道,并引入脉冲修正罚函数处理弹道倾角入轨条件,形成无约束最优化问题。借助于MATLAB集成遗传算法,实现了SSO发射轨道的优化设计。算例表明:该优化方法收敛性好,转移轨道的入轨条件能够精确满足,SSO的入轨参数只需较小的速度修正,优化结果曲线符合工程实际情况,得到了工业部门的认可。 |
| 关键词:
SSO发射轨道
优化
自适应积分
脉冲修正罚函数
遗传算法
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| Optimization of Launch Trajectory for SSO (Sun Synchronous Orbit) Based on Adaptive Transfer Orbit |
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| Dan Xue1,2, Yue Xiaokui1,2 |
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1. College of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. National Key Laboratory of Aerospace Flight Dynamics, Xi'an 710072, China |
| Abstract: |
| The optimal ascent trajectory design of the vehicle for Sun Synchronous Orbit(SSO) is an optimal control problem with strict inner and terminal constraints and variable final time; this is difficult for the optimal control theory. To solve this problem,firstly it is translated into a multi-parameter optimization problem,and then an adaptive integration module is presented to obtain a transfer orbit with altitude and velocity injection constraints automatically satisfied,and an impulse modified penalized function is introduced to deal with unsatisfied constraints. Finally,with the help of MATLAB integrated genetic algorithm(GA),the optimal ascent trajectory is obtained. A simulation example indicates that: the injection constraints of transfer orbit are met accurately,and those of SSO need a little modification in velocity magnitude. The obtained trajectories are consistent with actual engineering conditions,and have been approved by the administrative department for relevant industry. |
| Key words:
computer simulation
constrained optimization
design
genetic algorithms
MATLAB
orbital transfer
parameterization
schematic diagrams
adaptive transfer orbit
impulse modified
penalized function
SSO(Sun Synchronous Orbit) launch trajectory
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| 收稿日期: 2013-03-06
修回日期:
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| DOI: |
| 基金项目: 国家自然科学基金(11172235);高等学校博士点专项科研基金(20106102110003)资助 |
| 通讯作者:
Email： |
| 作者简介: 淡雪(1985-),女,西北工业大学博士研究生,主要从事飞行器动力学与相对导航研究。
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| 作者相关文章 |
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| 淡雪 在本刊中的所有文章 |
| 岳晓奎 在本刊中的所有文章 |
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参考文献: |
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[2] Rahn M, Thomas U M.Decomposition Algorithm for Performance Optimization of a Launch Vehicle.Journal of Spacecraft and Rockets, 1996, 33: 214-221
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[4] 罗亚中, 唐国金, 梁彦刚.基于分解策略的 SSO 发射轨道遗传全局优化设计.航空学报, 2004, 25(5): 443-446 Luo Yazhong, Tang Guojin, Liang Yangang.Decomposition Approach and Genetic Algorithm Based Global Optimization of Launch Trajectory for Sun Synchronous Orbit.Acta Aeronautica et Astronautica Sinica, 2004, 25(5): 443-446 (in Chinese)
[5] 贾沛然, 陈克俊, 何 力.远程火箭弹道学.长沙: 国防科技大学出版社, 1993 Jia Peiran, Chen Kejun, He Li.The Long-Range Rocket Ballistics.Changsha: National University of Defense Technology Press, 1993 (in Chinese)
[6] 宋忠保.导弹与航天丛书探空火箭设计.北京: 宇航出版社, 1993 Song Zhongbao.Missile and Aerospace Series the Design for Sounding Rocket.Beijing: China Astronautic Publishing House,1993 (in Chinese) |
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