基于导航接收机的自旋卫星姿态确定方法  

Navigation Receiver Based Attitude Determination for Spinning Satellites

作　　者：王伟[1] 方宝东 彭玉明[1] 

机构地区：[1]上海卫星工程研究所,上海200240

出　　处：《上海航天》2015年第4期8-12,58,共6页Aerospace Shanghai

基　　金：上海市重点实验室项目(13DZ2260100)

摘　　要：提出了一种基于单天线导航接收机跟踪环路载波相位差的自旋卫星姿态确定方法。以导航接收机锁相环鉴别器输出的载波相位差为数据源,推导了从载波相位变化中获得卫星姿态信息的算法模型。在天线安装半径0.3m,自旋速率20r/min,载波相位测量误差3mm,角速率测量误差0.1(°)/s条件下进行仿真,获得自旋卫星主轴在空间惯性坐标系中的定向精度为2.17°。研究表明用单天线导航接收机确定对低转速、低精度角速率陀螺自旋卫星姿态是可行的,与传统多天线接收机载波相位差测量方法相比,有体积小、低能耗和避免整周模糊度计算等优点。An attitude determination method for spinning satellites based on the carrier phase differences from a navigation receiver tracking loop with a single antenna was studied in this paper. The algorithm model of determining the spinning satellite＇s attitude from the carrier phase differences outputted by the phase-locked loop discrimination was given out. The simulation was done under the conditions of an antenna radius of 0. 3 m, a rotation rate of 20 r/min, carrier phase error 3 mm and angular velocity error 0.1（°）/s, the gained vector of the spinning axis of the satellite had an error of 2.17°. The study showed that it was feasible that using a navigation receiver with a single antenna could determine the attitude of the spinning satellites with low angular velocity and low precise gyroscope. The new method would have advantages of smaller size, less power and no integer ambiguity resolved compared with the traditional methods of multi-antenna.

关 键 词：自旋卫星 姿态确定 导航接收机 载波相位差 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]