基于微分进化算法的深空轨道全局优化设计

张仁勇; 罗建军; 程潏; 唐歌实; 曹静; 苏二龙; 冯晶琅

doi:10.6052/0459-1879-12-012

基于微分进化算法的深空轨道全局优化设计

1.
西北工业大学航天学院, 航天飞行动力学技术重点实验室,西安 710072
2. 北京航天飞行控制中心, 航天飞行动力学技术重点实验室,北京 100094

详细信息

通讯作者:
张仁勇

中图分类号: V412.4+1
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出版历程
- 收稿日期: 2012-01-03
- 修回日期: 2012-06-20
- 刊出日期: 2012-11-17

THE GLOBAL OPTIMIZATION OF SPACE EXPLORATION TRAJECTORY DESIGN BASED ON DIFFERENTIAL EVOLUTION ALGORITHM

1.
School of Astronautics, Northwestern Polytechnical University, National Key Laboratory of Aerospace Flight Dynamics,Xi'an 710072, China
2. Beijing Aerospace Control Center, National Key Laboratory of Aerospace Flight Dynamics, Beijing 100094, China

摘要

摘要: 针对多目标多任务的深空探测轨道设计问题,提出一种新的将探测目标、探测方式、探测顺序以及发射窗口同时作为优化变量, 并采用微分进化算法进行全局优化的设计方法. 使用该方法在只考虑太阳中心引力作用的二体模型下,基于圆锥曲线拼接法建立第三届全国深空轨道设计竞赛问题的优化模型并进行求解. 最后利用该方法求解ESA的ACT研究团队的深空探测任务算例并对结果进行对比分析. 结果表明, 提出的全局优化设计方法对解决多目标、多任务深空探测轨道优化设计问题是可行和有效的.
- 深空探测 /
- 多目标多任务 /
- 轨道优化 /
- Lambert变轨 /
- 微分进化算法
Abstract: In this paper, a new global optimization method is proposed to solve the multi-target space exploration trajectory design problem. The variables of targets selection, visiting sequences and launch windows are synchronously optimized. In the context of two-body model in which the central gravity of the sun is only considered with the thrust as impulse, the patched-conic method accompanied with differential evolution (DE) algorithm are applied to solve the global optimization trajectory design problem. Then the method is utilized to solve the problem of the Third National Design Competition for Deep Space Exploration and the example missions of the ACT of ESA. It proves that the global trajectory optimization design method is feasible and valuable for the problem of multi-target and multi-mission space trajectory design.
- deep space exploration /
- multi-target and multi-mission /
- trajectory optimization /
- lambert orbital transfer /
- di甧rential evolution (DE) algorithm

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参考文献(8)

唐忠兴, 崔红正, 刘哲等. 基于Lambert变轨的多任务深空探测轨道优化设计. 宇航动力学学报,2011,1(1):32-36 (Tang Zhongxing,Cui Hongzheng,Liu Zhe,et al. Trajectory optimal design for multi-mission deep space exploration based on lambert orbital transfer. Journal of Astrodynamics, 2011, 1(1): 32-36(in Chinese))

Olds AD, Kluever CA, Cupples ML. Interplanetary mission design using differential evolution. Journal of Spacecraft and Rockets, 2007, 44 (5): 1060-1070

Janin G. Trajectory design for the solar orbiter mission. Monografimath as de la Real Academia de Ciencias de Zaragoza, 2004, 25: 177-218

Vasile M, Locatelli M. A hybrid multiagent approach for global trajectory optimization. Journal of Global Optimization, 2009, 44(4): 461-479

Vasile M, Minisci E. On testing global optimization algorithms for space trajectory design. In: Proceeding of AIAA/AAS Astrodynamics Specialist Conference and Exhibit, Honolulu, Hawaii, August 18-21, 2008

Zhu KJ, Li JF, Baoyin HX. Multi-swingby optimization of mission to Saturn using global optimization algorithms.Acta Mechanica Sinica, 2009, 25: 839-845

Myatt DR, Becerra VM, Nasuto SJ, et al. Advanced global optimisation for mission analysis and design. ACT Contractor Report, www.esa.int/act, 2007

陈杨,唐歌实,李黎等. 第三届全国深空轨道设计竞赛总结,力学与实践,2012, 34(2): 97-101(Chen Yang, Tang Geshi, Li Li, et al. Summarization of third national design competition for deep space exploration. Mechanics in Engineering, 2012, 34(2): 97-101(in Chinese))