[an error occurred while processing this directive]
���¿��ټ��� �߼�����
   ��ҳ  �ڿ�����  ��ί��  Ͷ��ָ��  �ڿ�����  ��������  �� �� ��  ��ϵ����
�������պ����ѧѧ�� 2004, Vol. 30 Issue (06) :489-492    DOI:
���� ����Ŀ¼ | ����Ŀ¼ | ������� | �߼����� << | >>
����1, ����ʤ2*
1. �������պ����ѧ �ѧԺ, ���� 100083;
2. �������պ����ѧ ��е���̼��Զ���ѧԺ, ���� 100083
Steering law design for SGCMGs taking gimbal servo characteristics into account
Wu Zhong1, Chou Wusheng2*
1. School of Astronautics, Beijing University of Aeronautics and Astronautics�� Beijing 100083, China;
2. School of Mechanical Engineering and Automation, Beijing University of Aeronautics and Astronautics�� Beijing 100083, China

Download: PDF (0KB)   HTML 1KB   Export: BibTeX or EndNote (RIS)      Supporting Info
ժҪ �ڵ���ܿ�����������(SGCMG)ϵͳ�����ɵ������,ͨ���ٶ�����ŷ�ϵͳ����������ŷ���������.Ȼ��,����ŷ�ϵͳ���޵Ĵ����ʵ�ʴ��ڵĸ����Ŷ����ض���ʹ����������½�.Ϊ����SGCMG����ŷ����ԶԲ������ܵ�Ӱ��,�����һ�����Ͳ�����.�ò������ۺϿ�����SGCMGϵͳ�˶�ѧ�Ͷ���ѧ����,���Ը��ݺ�������̬���Ƹ����ĽǶ���(������)ָ��,ֱ�Ӽ����ÿ��SGCMG�������ϵͳ����Ŀ�������.���ڲ�����û���㷨����,��SGCMGϵͳ�������˶�����������,��ʹ�������ָ����������.ͬʱ,��������ʽ��,����ʵ��.Ӧ���ں������ϵ�ij4-SGCMGϵͳ�ķ���������,�����������ǿ��е�.
Email Alert
�ؼ����� ������   ������������   ��̬����   ������     
Abstract�� Gimbal servo systems of single gimbal control moment gyroscopes (SGCMGs) are often assumed to have ideal tracking performance during the steering law design. The tracking performance can be decreased due to the finite bandwidth and various disturbances of gimbal servo systems. In order to attenuate the effect of gimbal servo systems on steering performance, a new steering law was presented. This steering law was designed not only based on kinematics, but also dynamics of SGCMGs, and could calculate the control torque for each SGCMG gimbal directly according to the momentum (or torque) command. Since it has no arithmetic singularity, steering error can be made converge to zero exponentially when system singularities do not appear. Comparatively, it has a simple form and is easy to be realized. Simulation results of a certain 4-SGCMG system indicate that the algorithm stated above is feasible.
Keywords�� spacecraft   control moment gyroscopes   attitude control   steering law     
Received 2003-01-09;


About author: �� ��(1970-),��,ɽ����ɽ��,������, wuzhong@buaa.edu.cn.
����, ����ʤ.���ǿ���ŷ�����ʱSGCMGϵͳ���������[J]  �������պ����ѧѧ��, 2004,V30(06): 489-492
Wu Zhong, Chou Wusheng.Steering law design for SGCMGs taking gimbal servo characteristics into account[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2004,V30(06): 489-492
http://bhxb.buaa.edu.cn//CN/     ��     http://bhxb.buaa.edu.cn//CN/Y2004/V30/I06/489
Copyright 2010 by �������պ����ѧѧ��