对地观测卫星有限推力快速轨道机动优化方法

余培军; 王维; 李建成

对地观测卫星有限推力快速轨道机动优化方法

宇航动力学国家重点实验室,西安 710043

详细信息

作者简介:
余培军(1966-),男,河南确山人,研究员,prince_xscc@vip.163.com.

中图分类号: V 556
计量
- 文章访问数: 3365
- HTML全文浏览量: 185
- PDF下载量: 1128
- 被引次数: 0
出版历程
- 收稿日期: 2010-09-10
- 网络出版日期: 2011-07-30

Optimization method of finite thrust emergency orbit maneuver for an earth observation satellite

School of Aerospace, Northwestern Polytechnical University, Xi-an 710072, China

摘要

摘要: 研究了对地观测卫星在有限推力作用下,快速轨道机动到目标区域上空的优化算法.分析了任务需求并选取两次点火的变轨方法,使算法更具普适性.推导出考虑J2摄动的三维空间的有限推力动力学方程.使用Lambert方法确定有限推力时间变量的取值范围,并在此基础上使用遗传算法进行优化,最终得到时间最优意义的优化结果.通过一个算例对整个优化算法做了验证.结果表明该算法精度高、计算时间短,适用于快速轨道机动任务.
- 快速轨道机动 /
- 有限推力 /
- Lambert算法 /
- 遗传算法
Abstract: The optimal emergency orbit maneuver method for an earth observation satellite was studied, which uses the finite thrust model. The mission requirement of the emergency orbit maneuver was investigated firstly. A twice orbital maneuver technique was adequately chosen to make the algorithm universal. The finite thrust dynamic equation in the three-dimensional space that considering the J2 perturbation was derived. The time variable-s span was given by solving the Lambert-s problem. The genetic algorithm was used as the optimization method to get a time optimal result. An emulation example was given to verify the method. The result shows the method has a high precise and can be get in a short time so it is available for the emergency orbit maneuver mission.
- emergency orbit maneuver /
- finite thrust /
- Lambert algorithm /
- genetic algorithms

HTML全文

参考文献(1)

[1] Pontani M.Simple method to determine globally optimal orbital transfers[J].Journal of Guidance,Control,and Dynamics,2009,32(3):899-914 [2] 石俊,韩潮.应急轨道机动变轨方案快速设计算法[J].北京航空航天大学学报,2007,33(4):388-391 Shi Jun,Han Chao.Quick algorithm for designing emergency orbital transfer scheme[J].Journal of Beijing University of Aeronautics and Astronautics,2007,33(4):388-391(in Chinese) [3] 周军,常燕.考虑地球扁率J2摄动影响的异面椭圆轨道多冲量最优交会[J].宇航学报,2008,29(2):82-85 Zhou Jun,Chang Yan.Optimal multiple-impulse rendezvous between non-coplanar elliptic orbits considering the J2 perturbation effects[J].Journal of Astronautics,2008,29(2):82-85(in Chinese) [4] 雷涛.有限推力作用下航天器轨道优化设计方法研究 .哈尔滨:哈尔滨工业大学航天学院,2009 Lei Tao.Study on optimal orbit design for spacecraft with finite thrust .Harbin:School of Aerospace,Harbin Institute of Technology,2009(in Chinese) [5] 梁新刚,杨涤.有限推力下时间最优轨道转移[J].航天控制,2007,25(1):46-51 Liang Xingang,Yang Di.Time-optimal orbital transfer under finite thrust[J].Aerospace Control,2007,25(1):46-51(in Chinese) [6] Zhu K,Li J,Baoyin H.Satellite scheduling considering maximum observation coverage time and minimum orbital transfer fuel cost[J].Acta Astronautica,2010,66(2):220-229 [7] Xue Dan,Li Junfeng,Baoyin Hexi,et al.Reachable domain for spacecraft with a single impulse[J].Journal of Guidance,Control and Dynamics,2010,33(3):934-942 [8] 杨希祥,李晓斌,肖飞,等.智能优化算法及其在飞行器优化设计领域的应用综述[J].宇航学报,2009,30(6):2052-2061 Yang Xixiang,Li Xiaobin,Xiao Fei,et al.Overview of intelligent optimization algorithm and its application in flight vehicles optimization design[J].Journal of Astronautics,2009,30(6):2052-2061(in Chinese) [9] Wuerl A,Crain T,Braden E B.Genetic algorithm and calculus of variations-based trajectory optimization technique[J].Journal of Spacecraft and Rockets,2003,40(6):882-888

施引文献

资源附件(0)

访问统计