[an error occurred while processing this directive]
   
 
���¿��ټ��� �߼�����
   ��ҳ  �ڿ�����  ��ί��  Ͷ��ָ��  �ڿ�����  ��������  �� �� ��  ��ϵ����
�������պ����ѧѧ�� 2005, Vol. 31 Issue (11) :1254-1258    DOI:
���� ����Ŀ¼ | ����Ŀ¼ | ������� | �߼����� << | >>
����ʸ���۲�ĺ������ֶ���Ϣ�ں϶��˷���
���Ӳ�, ������*
�������պ����ѧ ������ѧ���繤��ѧԺ, ���� 100083
Two-segment information fusion attitude determination method for spacecraft from vector observations
Yu Yanbo, Fang Jiancheng*
School of Instrument Science and Opto-electronics Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

ժҪ
�����
�������
Download: PDF (403KB)   HTML 1KB   Export: BibTeX or EndNote (RIS)      Supporting Info
ժҪ ��Ի���MEMS(΢����ϵͳ)���ݺ�CMOS APS���������ļ��ɹ���/�ǹ���̬ȷ��ϵͳ�ĵ;����ص�,�о��������ڸö���ϵͳ�Ļ���ʸ���۲�Ķ����㷨.��������/����������������ģʽ,��EKF(Extended Kalman Filter)��QUEST������REQUEST�ȼ������õĶ����㷨.���EKF������REQUEST�㷨�IJ�ͬ�ص㲢���ȷ�����㷨QUEST,����Ԫ��Ϊ��̬����,����̬���Ƶ�EKF�����ֱ���QUEST�㷨������REQUEST�㷨�������ں�,���һ�ֶַ���Ϣ�ںϵ���̬������:����Ư�ƹ������ϴ�ʱ,��EKF��QUEST���,���ٹ��Ƴ�����Ư��.������Ư������С��һ���̶�,���л�ΪEKF������REQUEST�㷨�ںϵ�˫���˲���.����ȽϽ������,���ֶַ���Ϣ�ںϵ���̬�������ȿ��Թ�����̬����Ҳ���Թ�������Ư��,���ܴﵽ�ܸߵĶ��˾���.
Service
�ѱ����Ƽ�������
�����ҵ����
�������ù�����
Email Alert
RSS
�����������
�ؼ����� ����   ��̬ȷ��   EKF   ˫���˲�   ��Ϣ�ں�   ʸ���۲�     
Abstract�� The low precision characters of the integrated inertial/stellar attitude determination system consists of MEMS (micro electromechanical systems) gyros and CMOS APS star sensor. For this question, the methods of attitude determination from vector observations which suitable for this system were studied. There are several attitude determination methods suitable for the gyro/star-sensor configuration such as EKF, QUEST and optimal REQEUST. According to the different characters between the EKF and optimal REQUEST and together with the single-frame method QUEST, the quaternion was used as the attitude parameter. A two-segment attitude estimator was presented: when the estimated error of gyro drift was large, the fusion mode of EKF and QUEST was used to estimate the gyro drift as soon as possible. When the estimated error of gyro drift reduces to some low extent, the filter was switched to the fusion mode of EKF and optimal REQUEST. The results of simulation show that the two-segment estimator can estimate not only the attitude parameter but also the gyro drift. The determination accuracy of the attitude estimator can meet the attitude determination requirements of the most spacecrafts.
Keywords�� gyroscopes   attitude determination   EKF   dual filter   information fusion   vector observation     
Received 2004-11-17;
Fund:

������Ȼ��ѧ����������Ŀ(60174031); ���ú���Ԥ��������Ŀ

About author: ���Ӳ�(1974-),Ů,��������������,˶ʿ��, babera@163.com.
���ñ���:   
���Ӳ�, ������.����ʸ���۲�ĺ������ֶ���Ϣ�ں϶��˷���[J]  �������պ����ѧѧ��, 2005,V31(11): 1254-1258
Yu Yanbo, Fang Jiancheng.Two-segment information fusion attitude determination method for spacecraft from vector observations[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2005,V31(11): 1254-1258
���ӱ���:  
http://bhxb.buaa.edu.cn//CN/     ��     http://bhxb.buaa.edu.cn//CN/Y2005/V31/I11/1254
Copyright 2010 by �������պ����ѧѧ��