[an error occurred while processing this directive]
   
 
���¿��ټ��� �߼�����
   ��ҳ  �ڿ�����  ��ί��  Ͷ��ָ��  �ڿ�����  ��������  �� �� ��  ��ϵ����
�������պ����ѧѧ�� 2007, Vol. 33 Issue (09) :1051-1055    DOI:
���� ����Ŀ¼ | ����Ŀ¼ | ������� | �߼����� << | >>
ֱ����/���������Ͽ��Ƶ��� ����Ӧģ����ģ����
�����1, ������2*
1. �������պ����ѧ ���տ�ѧ�빤��ѧԺ, ���� 100083;
2. �������պ����ѧ �Զ�����ѧ���������ѧԺ, ���� 100083
Adaptive fuzzy sliding mode control for reaction-jet and aerodynamics compound control missile
Wu Zhenhui1, Dong Chaoyang2*
1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;
2. School of Automation Science and Electrical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

ժҪ
�����
�������
Download: PDF (0KB)   HTML 1KB   Export: BibTeX or EndNote (RIS)      Supporting Info
ժҪ ��Բ���ֱ����/���������Ͽ��Ƶ��������е�ǿ��Ϸ����Ե�����,�����һ�ֻ�������Ӧģ����ģ���Ƶ��Զ���ʻ����Ʒ���.�÷�����������Ӧģ��ϵͳ�����е����ܱƽ�����,�Դ󹥽Ƿ��й����е�������ѧϵͳ���ڵķ��������Խ��бƽ�,�����ñ�ṹ���ƶ������ŵ�ǿ³����,�������ϵͳ��ģ��,�˷��˱ƽ����������ŶԿ���ϵͳ��Ӱ��,ʵ���˶Դ����ָ��ľ�ȷ����.����������,����ƵĿ��Ʒ����Դ����ָ���нϺõĸ���Ч��,��ģ�Ͳ�ȷ���Ժ�������Ҳ���нϺõ�³����.���ڲ���ֱ����/���������Ͽ���,��Ч�ļ�С��������ƫ��,������������ı���.
Service
�ѱ����Ƽ�������
�����ҵ����
�������ù�����
Email Alert
RSS
�����������
�����
������
�ؼ����� ֱ����/���������Ͽ���   ��ģ����   ����Ӧģ��ϵͳ   �����Զ���ʻ��     
Abstract�� A missile autopilot design method based on adaptive fuzzy sliding mode control (AFSMC) was proposed for reaction-jet and aerodynamics compound control missile with nonlinearity and strong coupling. The universal approximation ability of adaptive fuzzy system was used to approximate the nonlinear function in missile dynamics equation during the flight of high angle of attack. And because the sliding mode control was robustness to external disturbance strongly, the sliding mode surface of the error system was constructed to overcome the influence of approximation error and external disturbance so that the actual overload can track the maneuvering command with high precision. Simulation results show that the missile autopilot designed in this paper not only can track large overload command with higher precision than traditional methods, but also is robust to model uncertainty and external disturbance strongly. After employing the reaction-jet and aerodynamics compound control, the aerodynamic fin deflection is decreased greatly. Therefore, the aerodynamic fin deflection saturation is avoided.
Keywords�� reaction jet and aerodynamics compound control   sliding mode control   adaptive fuzzy system   missile autopilot     
Received 2006-09-27;
Fund:

����֧�ż�������������Ŀ

About author: �����(1965-), ��, ������ɽ��, ��ʿ��, wuzhenhui100@126.com.
���ñ���:   
�����, ������.ֱ����/���������Ͽ��Ƶ��� ����Ӧģ����ģ����[J]  �������պ����ѧѧ��, 2007,V33(09): 1051-1055
Wu Zhenhui, Dong Chaoyang.Adaptive fuzzy sliding mode control for reaction-jet and aerodynamics compound control missile[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2007,V33(09): 1051-1055
���ӱ���:  
http://bhxb.buaa.edu.cn//CN/     ��     http://bhxb.buaa.edu.cn//CN/Y2007/V33/I09/1051
Copyright 2010 by �������պ����ѧѧ��