低轨大规模Walker通信星座构型控制仿真系统研究  

Research on the Configuration Control Simulation System of LEO Large-Scale Walker Communication Constellation

作　　者：李玖阳 胡敏 王许煜 云朝明 李奇 Li Jiuyang;Hu Min;Wang Xuyu;Yun Chaoming;Li Qi(Space Engineering University,Beijing 101416,China)

机构地区：[1]航天工程大学,北京101416

出　　处：《航天控制》2021年第3期69-75,共7页Aerospace Control

基　　金：国家自然科学基金(61403416)。

摘　　要：设计和开发了低轨(Low earth orbit,LEO)大规模Walker通信星座构型控制仿真系统,该系统分为轨道仿真分系统、构型维持分系统、在轨重构分系统和电推进离轨分系统4个部分,分别利用两次偏置法、考虑燃耗均衡性等指标的在轨重构方法和结合增广拉格朗日粒子群算法(Augmented lagrangian particle swarm optimization algorithm,ALPSO)的电推进离轨方法完成针对低轨大规模Walker通信星座的构型控制仿真。实例分析表明:系统将低轨大规模Walker通信星座的相对漂移控制在10年0.1°以内,得出燃料消耗均衡性等指标最优的重构方案,并利用电推进使失效卫星在3年内离轨。A low earth orbit(LEO)large-scale Walker communication constellation configuration control simulation system is designed and developed.The system can be divided into four parts:an orbit simulation subsystem,a configuration maintenance subsystem,an on-orbit reconstruction subsystem and an electric propulsion de-orbit subsystem.The twice-biases method,the on-orbit reconstruction method that involves fuel consumption balance and other indicators and the electric propulsion de-orbit method combined with the augmented lagrangian particle swarm optimization algorithm(ALPSO)are used separately to complete configuration control simulation for large-scale Walker communication constellations.Finally,the system is applied for completing the simulation analysis of the LEO large-scale Walker communication constellation.The case analysis result shows that the relative drift of the LEO large-scale Walker communication constellation is controlled within 0.1°in ten years by using this system,the optimum reconstruction plan based on fuel consumption balance and other indicators can be obtained and electric propulsion is used to de-orbit the failed satellite during the course of 3 years.

关 键 词：低轨 WALKER星座 过程仿真 构型控制 通信星座 

分 类 号：V412.2[航空宇航科学与技术—航空宇航推进理论与工程]