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�������պ����ѧѧ�� 2006, Vol. 32 Issue (08) :889-893    DOI:
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Autonomous orbit determination of spacecraft based on UKF using radar altimeter
Liu Jun, Han Chao*
School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

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Abstract�� The existing problem in using the extended Kalman filter(EKF) to estimate the state of one nonlinear system was discussed. And the unscented Kalman filter(UKF) was introduced, which is widely used today. The radar altimeter as a new measure instrument was introduced in the satellite orbit navigation based on star sensor. A algorithm was presented about the autonomous orbit determination with radar altimeter and star sensor. The complicated sea level model was established, and the influence of the gravity waves caused by wind was considered. Using the measure data recurring to radio altimeter and model of earth′s shape, the direction of earth-satellite vector in satellite orbit frame was calculated. Based on UKF the precision of autonomous navigation was improved obviously. The simulations demonstrate that the precision of the UKF is much higher than the EKF.
Keywords�� satellite   navigation   Kalman filter   radio altimeter     
Received 2005-10-19;
About author: �� ��(1980-),��,����������,��ʿ��, cooyangliu@163.com.
����, ����.����UKF���״�߶ȼ���������[J]  �������պ����ѧѧ��, 2006,V32(08): 889-893
Liu Jun, Han Chao.Autonomous orbit determination of spacecraft based on UKF using radar altimeter[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2006,V32(08): 889-893
http://bhxb.buaa.edu.cn//CN/     ��     http://bhxb.buaa.edu.cn//CN/Y2006/V32/I08/889
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