基于遗传算法的有限推力交会轨道优化仿真

摘要

For orbit optimization problem of final phase of rendezvous, a novel method based on genetic algorithm is proposed. The method is based on the C - W equations, which devides the whole final phase into several subarcs. In each subarc, the chaser takes a constant thrust, so the analytic solutions of the C - W equations can be achieved. Then the orbit optimization problem can be conversed into a mathematical programming problem with nonlinear constraints. In the end, the genetic algorithm is used to solve the mathematical programming problem. Mathematical simulation proves the effectiveness of the method.%针对有限推力空间飞行器交会对接逼近段燃料/时间组合最优轨道优化问题,提出了一种采用遗传算法求解的优化策略.以C-W方程为交会模型,将整个逼近段分为若干弧段,在每个弧段内追踪航天器均采用常值推力机动,这样可以求得C-W方程在每个弧段内的解析解,于是,交会对接逼近段的轨道优化问题可以转化为具有非线性约束的数学规划问题,最后采用广义拉格朗日-遗传算法对该问题进行了优化求解.数学仿真结果表明,该方法可以很好的解决交会对接终端逼近段燃料/时间组合最优轨道优化问题.