入轨精度对降交点地方时的影响分析  

Analysis of the Influence of Orbit Injection Accuracy on the LocalTime of Descending Node

作　　者：李伟建[1] 刘旭光 刘兴威[1] 邓海琴 Li Weijian;Liu Xuguang;Liu Xingwei;Deng Haiqin(Jiuquan Satellite Launch Center,Jiuquan 732750,China)

机构地区：[1]酒泉卫星发射中心,酒泉732750

出　　处：《航天控制》2023年第5期68-73,共6页Aerospace Control

摘　　要：先提出太阳同步轨道的设计方法和降交点地方时的计算方法,然后以降交点地方时偏差作为评价标准,采用正交试验设计方法分析入轨精度对其影响。实例计算结果表明,入轨偏差将导致降交点地方时随时间积累不断漂移,轨道倾角偏差对降交点地方时的影响最大,半长轴偏差的影响次之,而偏心率偏差的影响最小。Firstly,the design method of solar synchronous orbit and the calculation method of the local time of descending node are developed,and then the deviation of the local time of descending node is taken as the evaluation standard.The orthogonal experiment design method is used to analyze the influence of or⁃bit injection accuracy on the evaluation standard.The calculation results show that orbit injection deviation can cause the drift of the local time of descending node with time accumulation,the orbital inclination devi⁃ation has the greatest influence on the local time of descending node,and the influence of the semi⁃major axis deviation is taken the second place,while the eccentricity deviation is the least.

关 键 词：入轨精度 太阳同步轨道 降交点地方时 正交试验 

分 类 号：V474[航空宇航科学与技术—飞行器设计]