平动点Halo轨道航天器保持的多目标优化

Multi-objective optimization for spacecraft keeping on libration Halo orbit

针对日地系统平动点附近Halo轨道航天器保持任务,考虑航天器的能量消耗与轨道保持精度需求,采用多目标优化方法设计了改进时变控制器用于航天器Halo轨道保持任务。首先,基于圆形限制性三体模型推导了航天器的相对动力学方程并基于此设计了线性时变控制器。然后,采用多目标优化方法对时变控制器参数进行优化,得到满足航天器能量消耗与轨道保持精度之间平衡的Pareto最优解。最后,通过对考虑模型与环境干扰情况的数值模拟,结果表明多目标优化方法对平动点Halo轨道航天器保持任务达到低能能耗与高精度目标,具有一定的应用价值。

As the stabilization missions of the spacecraft on libration point Halo orbits of Sun-Earth system,energy consumption and orbit maintaining precision are their contradict objectives. This paper proposed a multi-objective optimization method to design time-varying controller in the Halo orbit stabilization missions. Firstly, a time-varying controller, based on the linearization CRTBP model,is constructed. Then,the weighting matrix elements of the controller are optimized with multi-objective algorithm. Finally,a study case,considering environment errors,is optimized and the Pareto fronts of the optimization results, showing the trade-off between the fuel consumption and orbit maintaining, prove the feasibility of this method.