一种重访时间约束的卫星轨道与星座设计方法  

A Revisiting Time-Constrained Satellite Orbit and Constellation Design Method

作　　者：李伟建[1] 刘旭光 刘兴威[1] 刘裕贵 LI Wei-jian;LIU Xu-guang;LIU Xing-wei;LIU Yu-gui(Jiuquan Satellite Launch Center,Jiuquan Gansu 732750,China)

机构地区：[1]酒泉卫星发射中心,甘肃酒泉732750

出　　处：《计算机仿真》2023年第5期69-72,共4页Computer Simulation

摘　　要：卫星轨道与星座设计在航天发射活动中具有重要作用和地位。针对对地观测任务需求,先研究卫星轨道设计的理论方法,明确卫星轨道设计的步骤和全过程,包括轨道外推、星下点计算、探测区域计算、目标区域离散化等计算过程;然后采用Matlab/STK联合仿真的方法实现星座设计与星座性能求解,对设计变量的迭代搜索确定设计域内满足任务要求的星座参数;最后通过星座性能参数的比较可以获得较优的星座参数。上述方法简单,能适应卫星轨道与星座设计的复杂问题。Satellite orbit and constellation design has an important role and position in space launch activities.Ac-cording to the requirements of Earth observation task,the theoretical method of satellite orbit design is studied firstly,clarifying the steps and the whole process of satellite orbit design,which computational process includes orbital ex-trapolation,substellar point calculation,detection region calculation,target region discretization,etc.The constella-tion design and constellation performance solution are realized using the Matlab/STK joint simulation method.The it-erative search of design variables can determine the constellation parameters within the design domain that meet the task requirements.Finally,the superior constellation parameters can be obtained by comparison of constellation per-formance parameters.The method is simple,and it is adaptable to the complex problem of satellite orbit and constel-lation design.

关 键 词：轨道设计 重访时间 仿真 

分 类 号：TP391.9[自动化与计算机技术—计算机应用技术]