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�������պ����ѧѧ�� 2012, Vol. 38 Issue (6) :726-730    DOI:
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Carrier phase/SINS integrated navigation for spacecraft on high earth orbit
Wen Yongzhi, Wu Jie*
College of Aerospace and Material Engineering, National University of Defense Technology, Changsha 410073, China

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Abstract�� Because of the fewer available satellites and the greater wastage of signal on space link, the measurement accuracy is lower using pseudo-distance. The method of autonomous navigation using carrier phase of global navigation satellite system(GNSS) and strapdown inertial navigation system (SINS) was presented for the high earth orbit automotive spacecraft. The float solutions of initial integer ambiguity were used as states variable in this method, and the nonlinear filter was established by square-root unscented Kalman filter (SRUKF). The method of cycle slips faults detection and isolation was presented based on the intersections of the float solutions. The method of integrated navigation makes full use of the high measurement accuracy of carrier phase and slowly varying characteristic of systematic errors, and it can increase the reliability and the precision of the navigation system.
Keywords�� carrier phase   strapdown inertial navigation system(SINS)   integrated navigation   fault detection and isolation     
Received 2011-03-03;
������, ���.�ز���λ/�����ߵ���϶Ը߹�������ĵ���[J]  �������պ����ѧѧ��, 2012,V38(6): 726-730
Wen Yongzhi, Wu Jie.Carrier phase/SINS integrated navigation for spacecraft on high earth orbit[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2012,V38(6): 726-730
http://bhxb.buaa.edu.cn//CN/     ��     http://bhxb.buaa.edu.cn//CN/Y2012/V38/I6/726
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