结合混合法与微分进化法的小推力轨道全局优化设计  

Effectively Designing and Optimizing Low-Thrust Trajectory with Differential Evolution Algorithm and Hybrid Method

作　　者：王星又[1] 岳晓奎[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《西北工业大学学报》2013年第5期689-694,共6页Journal of Northwestern Polytechnical University

基　　金：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

摘　　要：针对小推力行星际转移轨道的设计问题,提出了一种结合混合法与微分进化法的全局优化设计方法,并进行了改进。通过对推力方向角初值与方向角导数初值与加速度幅值的猜测对协态变量进行限制。通过对重生个体的调整确保所得解在可用范围,提高算法可靠性。在微分进化算法后期引入加入最优个体的改进变异操作提高收敛速度。引入退火策略及权重处理确保算法讯速得到满足约束条件的最优解。以地球-水星小推力"推-滑-推"燃料最省转移轨道为例进行了验证,并基于同一仿真实例应用原模型及其它优化算法进行了仿真并对其结果进行了比较。仿真结果表明:该优化设计模型能快速,有效地寻找到最优轨迹,对深空探测轨道优化设计问题具有良好的通用性、先进性与工程运用参考价值。An optimization and design approach for low-thrust trajectory based on modified differential evolution and hybrid method, believed to be effective, is proposed. First, the initial values of thrust and the magnitude of thrust acceleration are guessed to reduce variation ranges of co-state variable values. Then the trial vector adjustment strat- egy is introduced into differential evolution process to keep the optimization variables from boundary violation and enhance the reliability. In order to improve the convergence efficiency, a mutation operation with best individual in- formation is proposed in the terminal part of differential evolution. Annealing strategy and weighting method are used in constraint management to accelerate the converging process and to better satisfy constraints. We, taking op- timal-fuel low-thrust transfer from earth to mercury as an example, validate the new method. The simulation results and their analysis demonstrate preliminarily that the proposed method is indeed effective for finding the global opti- mal transfer trajectory and has higher reliability. This method may be widely used in engineering problems on global optimization of dynamic and static parameters.

关 键 词：加速 有效性 设计 有约束优化 微分进化算法 全局优化 小推力 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]