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本文提出使用姿态敏感器作为测量仪器,结合星载计算机来完成自主卫星导航(ASN)和轨道保持的方法。根据平均轨道根数理论和测量关系式建立ASN离散、线性化数学模型,利用条件正态过程的滤波定理,证明在有轨道控制和敏感器跟踪的条件下,轨道变量的递推滤波仍具有无偏最小方差特性。另外,针对姿态确定随机误差对ASN系统的影响,给出一种自适应自主导航算法选。择典型的地球探测卫星轨道,进行Monte-Carlo模拟,结果表明:系统工作性能良好。
This paper presents a method of using Attitude Sensor as a measuring instrument and combining satellite-borne computer with autonomous satellite navigation (ASN) and orbit keeping. According to the average orbital root number theory and the measurement relation, a discrete and linearized mathematical model of ASN is established. By using the filtering theorem of conditional normal process, it is proved that the recursive filtering of the orbit variables still has no effect on the track control and sensor tracking Partial minimum variance characteristics. In addition, aiming at the influence of attitude error on ASN system, an adaptive autonomous navigation algorithm is proposed. Select typical earth exploration satellite orbit, Monte-Carlo simulation, the results show that: the system works well.