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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。
A method of attitude determination of spin satellite based on the phase difference of the carrier of the single antenna navigation receiver is proposed. The phase difference of the carrier output from the PLL was used as the data source, and the algorithm model of obtaining satellite attitude information from the carrier phase variation was derived. The orientation accuracy of spin satellite main shaft in space inertial coordinate system was obtained with antenna installation radius of 0.3 m, spin rate of 20 r / min, carrier phase measurement error of 3 mm and angular rate error of measurement of 0.1 (°) / s 2.17 °. The research shows that it is feasible to determine satellite attitude of low-speed and low-precision angular rate gyro with single-antenna navigation receiver. Compared with the traditional multi-antenna receiver phase difference measurement method, it has the advantages of small size, low power consumption and avoiding the whole week Ambiguity calculation and so on.