编队卫星短弧段相对轨道确定方法研究  

Study on Relative Orbit Determination Method of Satellites Formation with Short-arc

作　　者：李晓明[1] 曾国强[1] 姚红[1] 

机构地区：[1]装备指挥技术学院,北京101416

出　　处：《航天控制》2009年第5期48-51,57,共5页Aerospace Control

摘　　要：针对2颗星编队飞行的情况,描述了相对运动的3种动力学模型,利用GPS测量得到的相对位置矢量,选择了非线性最小二乘估计方法来实现相对轨道确定。结合空间圆编队构形进行了分析和仿真,结果表明该方法能得到高精度的相对状态信息,相对动力学模型越精确,相对状态信息精度越高。Aiming at the situation of two-satellite formation flying, three relative dynamics models are described by using the relative position vector based on GPS measurement and selects nonlinear least squares estimation method for the determination of relative orbit. Taking a circle formation as an example, the simulation and analytical results show that this method can provide high precision relative states, and the better relative dynamics model makes the relative states more accurate.

关 键 词：编队卫星 相对轨道确定 动力学模型 短弧段 非线性最小二乘估计 

分 类 号：V448[航空宇航科学与技术—飞行器设计]