小卫星鲁棒优化轨道设计方法研究  

Research on Robust Optimal Orbit Design Method for Small

作　　者：孙飞 李新洪 SUN Fei;LI Xin-hong(Department of Graduate Management,Space Engineering University,Beijing 101416,China;Department of Aerospace Science and Technology,Space Engineering University,Beijing 101416,China)

机构地区：[1]航天工程大学研究生院,北京101416 [2]航天工程大学宇航科学与技术系,北京101416

出　　处：《计算机仿真》2023年第3期41-46,102,共7页Computer Simulation

摘　　要：研究受大气阻力不确定性影响的小卫星轨道设计问题,给出一种对大气系数变化相对稳定的鲁棒轨道设计方法。考虑到大气阻力不确定性对轨道设计的不利影响,最佳解决方案将最大化给定目标站点的观测持续时间,对大气系数的显著变化具有一定的鲁棒性。最大目标观测时间受到每个站点的优先级和最小观测持续时间的限制,将鲁棒优化模型和多目标优化算法结合,最大化给定站点的观测持续时间。蒙特卡罗仿真结果表明,与传统单目标随机优化算法所获得的标称轨道解相比,设计得到的鲁棒轨道解具有更好的稳定性,验证了轨道设计方法的有效性。This paper focuses on the small satellite orbit design problem affected by atmospheric drag uncertainty,and gives a robust orbit design method that is relatively stable to atmospheric coefficient variations.The maximum target observation time is limited by the priority of each station and the minimum observation duration.Considering the adverse effect of atmospheric drag uncertainty on the orbit design,this paper combines a robust optimization model and a multi-objective optimization algorithm,so as to maximize the observation duration for a given station.The Monte Carlo simulation results show that the robust orbit solution obtained from the design of this paper has better stability,compared with the nominal orbit solution obtained from the conventional single-objective stochastic optimization algorithm,which verifies the effectiveness of the method.

关 键 词：小卫星轨道设计 鲁棒优化方案 蒙特卡罗仿真 多目标优化算法 

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]