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�������պ����ѧѧ�� 2011, Vol. 37 Issue (4) :462-465    DOI:
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Investigation on inertial platform multi-position rolling self-calibration
Bao Weimin, Shen Gongxun, Li Huabin*
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Abstract�� The guidance instrument errors are the main factors of reducing the hitting accuracy of inertial-guided missile. The measuring error of inertial platform is the major part. So the multi-position rolling self-calibration approach for inertial platform was studied. The gyroscope error models and the accelerometer error models were firstly built, and multi-position rolling self-calibration test was designed. Based on the scheme, numerical multi-position rolling self-calibration simulations were conducted, and influence factors were anglicized. Simulation results show that this approach can effectively separate the error coefficients. Under normal locked errors, the error coefficients separation precision is better than 99%, accordingly, the hitting accuracy of missile is increased.
Keywords�� inertial platform   multi-position rolling   self-calibration   test design     
Received 2010-05-22;
About author: ��Ϊ��(1960-),��,�㽭����,��ʿ��,baoweimin@163.com.
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��Ϊ��, �깦ѫ, ���.����ƽ̨��ϵͳ�ж�λ�÷����Ա궨����[J]  �������պ����ѧѧ��, 2011,V37(4): 462-465
Bao Weimin, Shen Gongxun, Li Huabin.Investigation on inertial platform multi-position rolling self-calibration[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2011,V37(4): 462-465
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http://bhxb.buaa.edu.cn//CN/     ��     http://bhxb.buaa.edu.cn//CN/Y2011/V37/I4/462
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