自主轨道确定中日月摄动对卫星轨道倾角的影响  

Lunisolar Perturbation in Autonomous Orbit Determination for Satellite

作　　者：薛申芳[1] 金声震[2] 宁书年[1] 孙才红[2] 

机构地区：[1]中国矿业大学,北京100083 [2]国家天文台,北京100012

出　　处：《计算机仿真》2004年第10期28-30,37,共4页Computer Simulation

基　　金：中国科学院科技创新基金支持项目(No.CXJJ-84)

摘　　要：利用天文方法和天文技术实现卫星自主轨道确定越来越倍受关注,而日月引力对高轨道卫星而言是一种很重要的一种摄动力,且随着卫星高度的增加对卫星的影响越加明显。该文针对组合大视场星敏感器卫星自主定轨天文方法,建立了日月引力摄动下的卫星自主轨道确定的广义卡尔曼滤波仿真模型,包括状态模型和观测模型,对东方红三号(DFH-3)地球同步轨道通讯卫星,在取初始轨道升交角分别为0°、90°和270°三种情况进行了仿真,得到了在日月摄动下卫星轨道倾角的变化规律,且把计算结果与已有的东方红三号卫星数据进行了比较。An attention is more and more paid to atonomous orbit determination for satellite with the astronomical method and technology.The lunisolar gravitation is an important perturbation to high orbit satellite,and the influence of the perturbation is more and more obvious along with the increment of satellite's altitude. This paper gives expanded Kalman filtering model under lunisolar gravitation aiming at the autonomous orbit determination for satellite with large field of view star sensors, the calculator simulation to DFH-3 satellite and the comparison of the calculated results with existing results of DFH-3 satellite under three kinds of circumstances of right ascension of the ascending node of 0°,90°and 270°. The changed regulation of orbital inclination under the action of lunisolar gravitation is shown.

关 键 词：组合大视场星敏感器 自主定轨 卡尔曼滤波 日月摄动 

分 类 号：V1[航空宇航科学与技术—人机与环境工程]