[an error occurred while processing this directive]
���¿��ټ��� �߼�����
   ��ҳ  �ڿ�����  ��ί��  Ͷ��ָ��  �ڿ�����  ��������  �� �� ��  ��ϵ����
�������պ����ѧѧ�� 2003, Vol. 29 Issue (5) :428-433    DOI:
���� ����Ŀ¼ | ����Ŀ¼ | ������� | �߼����� << | >>
������, ���ڻ�*
�������պ����ѧ �Զ�����ѧ���������ѧԺ
Control Law Reconfiguration under Control Surface Failure �� for Nonlinear Aircraft Dynamic
Li Weiqi, Chen Zongji*
School of Automation Science and Electrical Engineering, Beijing University of Aeronautics and Astronautics

Download: PDF (0KB)   HTML 1KB   Export: BibTeX or EndNote (RIS)      Supporting Info
ժҪ �о��������ɶȷ����Է��������ķɻ��ڲ��������˻������������ʹ��α�淨���п��� ���ع��ķ���.ͨ��������ϵ���еIJ��ݵ������к���Ľ��ƴ���,���������ع�����ת�� Ϊ��һ�����Է����������.������ȫ����ʵʱ������,��֤�˸��ع��㷨�Ŀ�����.
Email Alert
�ؼ����� ���п���   �ݴ���   ������   ���޸����п���ϵͳ   �������ع�     
Abstract�� The application of pseudo-inverse method based flight control reconfiguration i n the 6 degrees of freedom aircraft model was introduced. The failure considered here is the control surface effectiveness loss or lock-in-place. Via the appro priate linearization of the control coefficients, the reconfiguration problem wa s simplified to a problem of solving a linear equations. The real-time digital simulation results were given to indicate the validity of the algorithm.
Keywords�� flight control   fault-tolerant technique   control surfaces   self-r epair flight control system   control law reconfigure     
Received 2002-03-01;


About author: ������(1976-),��,����������,��ʿ��,100083,����.
������, ���ڻ�.�����Էɻ������������ϵĿ������ع�[J]  �������պ����ѧѧ��, 2003,V29(5): 428-433
Li Weiqi, Chen Zongji.Control Law Reconfiguration under Control Surface Failure �� for Nonlinear Aircraft Dynamic[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2003,V29(5): 428-433
http://bhxb.buaa.edu.cn//CN/     ��     http://bhxb.buaa.edu.cn//CN/Y2003/V29/I5/428
Copyright 2010 by �������պ����ѧѧ��