基于微分进化算法的深空小推力轨道优化设计

Optimal Design of Deep Space Low-Thrust Trajectory Based on Differential Evolution

针对多目标多任务的深空探测轨道优化设计问题,基于以太阳为主引力体的二体模型,采用电推进小推力系统,提出了将目标行星的探测方式、探测顺序、发射窗口同时进行全局优化的解决方案。依此建立小推力轨道优化设计算法模型,利用微分进化算法进行全局一体化优化设计,得出多目标多任务的一体化深空探测轨道。通过与相同条件下其他设计方法的结果比对分析得出:基于小推力推进方式并采用微分进化算法进行优化的轨道优化设计方案,在多目标多任务深空轨道一体化设计问题上具有可行性及应用价值。

Based on the assumption of two body model that takes into consideration only the central gravity of the sun, a solution featuring global optimization of target planet exploration modes, exploration sequence and launch windows is proposed to meet requirements of trajectory design and optimization for multi target and muhi-mission deep space exploration, using an electrical low thrust propulsion system. An algorithm model is developed for opti- mal design of low thrust trajectory and a differential evolution algorithm is used for integrated optimal global design. As a result, an integrated multi target and multi mission deep space exploration trajectory is obtained. Cornpared with the results of other design methods under the same conditions, the proposed solution is feasible and is of high value to integrated multi-target and muhi-mission deep space trajectory design.