Optimal correction strategy during Lambert transfer from view of probability
-
摘要: 应用Monte-Carlo法和遗传算法的联合仿真求解Lambert转移中途修正的全局概率最优策略.首先推广限制性三体问题中求解周期性特解的微分修正算法构造出考虑J2项摄动下的Lambert转移轨道并以此作为参考轨迹,则中途修正策略仅需针对导航误差、初始偏差修正的控制偏差等进行补偿.应用微分修正算法导出的单值矩阵,设计出3类线性和非线性中途修正策略,以适应不同的精度需要.随后应用Monte-Carlo和遗传算法的联合仿真,可以得到实现代价函数(落点误差最小)在概率意义下的最优解.与直接利用优化算法寻优需要已知各种误差量不同,得到的最优修正策略更具有普适性.
-
关键词:
- Lambert转移 /
- 微分修正 /
- 中途修正 /
- Monte-Carlo法 /
- 遗传算法
Abstract: Monte-Carlo simulation and genetic algorithm were employed to achieve the optimal correction strategy during Lambert transfer from the view of probability. The Lambert trajectory associated J2 perturbation was generated from differential correction algorithm that was used to yield the periodic orbit in circular restricted three body problem (CR3BP). So the correction maneuvers dealt with just the residual errors from navigation and controller. Then the linear and nonlinear strategies were derived from the monodromy matrix of differential correction algorithm, and then the Monte-Carlo simulation and genetic algorithm were employed to minimize the rendezvous errors from the view of probability. Quite different from the traditional strategies, the correction developed is universal for its robustness to measure errors. -
[1] Battin R H.An introduction to the mathematics and methods of astrodynamics [M].New York:AIAA Inc,1987 [2] 韩潮,谢华伟.空间交会中多圈Lambert变轨算法研究[J].中国空间科学技术,2004(5):9-14 Han Chao,Xie Huawei.Research on algorithm of loopy Lambert transfer in space rendezvous[J].Chinese Space Science and Technology,2004(5):9-14 (in Chinese) [3] Spencer D B,Kim Y H.Optimal spacecraft rendezvous using genetic algorithms[J].Journal of Spacecraft and Rockets,2002,39(6):859-865 [4] 陈统,徐世杰.基于遗传算法的最优Lambert双脉冲转移[J].北京航空航天大学学报,2007,33(3):273-274 Chen Tong,Xu Shijie.Optimal Lambert two-impulse transfer using genetic algorithm[J].Journal of Beijing University of Aeronautics and Astronautics,2007,33(3):273-274(in Chinese) [5] Xu Ming,Xu Shijie.Trajectory and correction maneuver during the transfer from Earth to Halo orbit [J].Chinese Journal of Aeronautics,2008,21(3):200-206 [6] Xu Ming,Xu Shijie.Nonlinear dynamical analysis for displaced orbits above a planet [J].Celestial Mechanics and Dynamical Astronomy,2008,102(4):327-353 [7] Xu Ming,Xu Shijie.Structure-preserving stabilization for Hamiltonian system and its applications in solar sail [J].Journal of Guidance,Control and Dynamics,2009,32(3):997-1004 [8] Xu Ming,Xu Shijie.J2 invariant relative orbits via differential correction algorithm [J].Acta Mechanica Sinica,2007,23(5):585-595 [9] Noton M.Spacecraft navigation and guidance [M].London:Springer,1998 -
点击查看大图
计量
- 文章访问数: 2677
- HTML全文浏览量: 167
- PDF下载量: 410
- 被引次数: 0
下载:
