[an error occurred while processing this directive]
   
 
���¿��ټ��� �߼�����
   ��ҳ  �ڿ�����  ��ί��  Ͷ��ָ��  �ڿ�����  ��������  �� �� ��  ��ϵ����
�������պ����ѧѧ�� 2011, Vol. 37 Issue (11) :1388-1394    DOI:
���� ����Ŀ¼ | ����Ŀ¼ | ������� | �߼����� << | >>
һ��ģ�����³����������̬ȷ������
κ����, �*
�������պ����ѧ �Զ�����ѧ���������ѧԺ, ���� 100191
Satellite attitude determination algorithm of model error robustness
Wei Mingkun, Yang Jing*
School of Automation Science and Electrical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

ժҪ
�����
�������
Download: PDF (516KB)   HTML 1KB   Export: BibTeX or EndNote (RIS)      Supporting Info
ժҪ ���һ�ֽ�Ϸ�����Ԥ���˲��Ͷ��ײ�ֵ�˲�ʵ�ֻ����ǹ�/���ݵĸ߾�����̬ȷ�������㷨.���㷨�÷�����Ԥ���˲�����ģ�����,�ٶԲ������ģ���ø߾��ȵĶ��ײ�ֵ�˲���������̬����.�����������ʵ�����������Ի����̬ȷ��ϵͳ�ľ�ȷ����ѧģ��,���ô�ͳEKF(Extended Kalman Filter)��ģ�������Ϊ���ֵ����������,�����˲����Ƚ���������ɢ������.ͬʱ,���ײ�ֵ�˲���������ģ�Ͱ��ն��׽���,������㺯��ƫ����,�õ��߾��ȵ�������̬����.������֤�˸÷�������Ч��ʵʱ���Ʋ�����ģ�����,�������̬���Ƶľ���,�ҹ��ƾ������˲����ڵ�Ӱ�첻��,�Ӷ���֤���㷨��³���Ժ���Ч��.
Service
�ѱ����Ƽ�������
�����ҵ����
�������ù�����
Email Alert
RSS
�����������
�ؼ����� �������˲�   ״̬����   ����   ��̬����     
Abstract�� A new high-precision star sensor/gyro attitude determination algorithm based on nonlinear predictive filter (NPF) and second-order divided difference filter was presented. In this algorithm, model error was estimated by NPF, and the state was estimated via second-order divided difference filter by using compensated system model. While it is difficult to obtain the accurate dynamic model of attitude determination system, extended Kalman filter (EKF) treated uncertain model error as zero-mean white noise might cause low precision of state estimation even to divergence. The proposed method solved such problem. The nonlinear model was the second-order approximation while using second-order divided difference filter without calculating the partial derivatives of system model, and then attitude estimation with high precision was obtained. Simulation results show that the proposed method estimates and compensates the model error in real-time effectively and improves the estimation precision, also the filter period influences the precision slightly. The effectiveness and the robustness of the proposed method are proved.
Keywords�� nonlinear filtering   state estimation   error compensation   attitude control     
Received 2010-06-25;
Fund:

������Ȼ��ѧ����������Ŀ(60704006)

About author: κ����(1984-), ��, �ӱ���ɽ��, ˶ʿ��, weimingkun2005@163.com.
���ñ���:   
κ����, �.һ��ģ�����³����������̬ȷ������[J]  �������պ����ѧѧ��, 2011,V37(11): 1388-1394
Wei Mingkun, Yang Jing.Satellite attitude determination algorithm of model error robustness[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2011,V37(11): 1388-1394
���ӱ���:  
http://bhxb.buaa.edu.cn//CN/     ��     http://bhxb.buaa.edu.cn//CN/Y2011/V37/I11/1388
Copyright 2010 by �������պ����ѧѧ��