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�������պ����ѧѧ�� 2007, Vol. 33 Issue (10) :1233-1236    DOI:
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Spacecraft attitude slew maneuver control via backstepping method
Zheng Minjie, Xu Shijie*
School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

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Abstract�� The backstepping control method was applied to the slew maneuver of the rigid spacecraft. In order to avoid the complicated calculation of the derivation of the intermediate control law which is required in the conventional backstepping method, the intermediate control law presents in a form of differential equation. On this basis, two methods were applied to reduce the requirement in the max actuator output torque by means of postponing the peak of the control torque. One method is to change the initialization of the intermediate control law. The other is to utilize a worse angular velocity tracking law. The system stability with the second control law depends on the parameters of the controller, however, the max control torque can be accurately restricted. Simulation results illuminate the availability of the derived control laws.
Keywords�� backstepping method   attitude control   slew maneuver     
Received 2006-11-03;
Fund:

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֣����,������.�����˲�������Ƶĺ�������̬��б��������[J]  �������պ����ѧѧ��, 2007,V33(10): 1233-1236
Zheng Minjie, Xu Shijie.Spacecraft attitude slew maneuver control via backstepping method[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2007,V33(10): 1233-1236
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