利用非合作航天器双特征结构的相对姿态确定方法  

Relative Attitude Determination Method of Non-Cooperative Spacecraft Using Dual Feature Structure

作　　者：王大轶[1] 鄂薇 邹元杰[1] 史纪鑫[1] 黄美丽[1] WANG Dayi;E Wei;ZOU Yuanjie;SHI Jixin;HUANG Meili(Beijing Institute of Spacecraft System Engineering,Beijing 100094)

机构地区：[1]北京空间飞行器总体设计部

出　　处：《飞控与探测》2020年第1期18-26,4,共9页Flight Control & Detection

基　　金：国家自然科学基金（61525301,61690215,61803027）

摘　　要：针对空间非合作航天器相对姿态确定难度大的问题,提出了一种利用非合作航天器双特征结构的相对姿态确定方法,该方法利用航天器的星箭对接环与太阳帆板结构进行联合定姿,首先基于投影同心圆代数约束关系计算星箭对接环所在平面法向量,进而基于平行线消失点原理计算太阳帆板旋转轴方向向量,能够在太阳帆板为旋转翼情况下进行相对姿态确定。利用包含星箭对接环与太阳帆板结构的失效翻滚航天器图像进行仿真验证,结果表明:该方法能够有效确定目标航天器的相对姿态,在4m观测距离下姿态角最大误差小于2°。For solving the problem of space non-cooperative target relative attitude determination,a relative attitude determination method of target spacecraft using dual feature structures is proposed.The docking ring and solar panel are selected as feature structures for relative attitude determination,and two feature structures and the relative attitude determination method are studied.The normal vector of docking ring is calculated based on concentric circular algebra constraint.The spindle vector of solar panel is calculated based on vanish point method.This method can be applied in rotor wing condition.The failed rolling spacecraft including docking ring and solar panel is used for verifying this method.The results show that this method can be used to determinate the relative attitude of target spacecraft,and the attitude angle errors are less than 2 degree at a distance of 4m.

关 键 词：非合作目标 特征结构 相对姿态确定 星箭对接环 太阳帆板 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]