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�������պ����ѧѧ�� 2010, Vol. 36 Issue (12) :1417-1421    DOI:
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2. �й�����Ƽ����Ź�˾ ��1�о�Ժ18��, ���� 100076
Design theory of thrust vector control servo mechanism for a type of spacecraft
Lu Hao1, Li Yunhua1, Zhu Chenglin2*
1. School of Automation Science and Electrical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. The 18th Institute of 1st Academe in China Aerospace Science & Technology Group Corporation, Beijing 100076, China

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Abstract�� Addressing the requirements of servo mechanism applied in a certain type of spacecraft, one servo mechanism for thrust vector control was designed. By comparing hydraulic servo mechanism,pneumatic servo mechanism and electric servo mechanism, their characteristics were obtained and the electric servo mechanism was selected. The key techniques of electric servo mechanism were researched, including the design of electromechanical actuators, drive and control technology and redundancy technology. The two-degree of freedom dynamics model of electric servo mechanism with two redundancies was established and its dynamic characteristics were simulated. Theory analysis and simulation results show that the scheme of electric servo mechanism is practical and logical. The electric servo mechanism not only meets the basic demands of the spacecraft, such as high reliability and good maintainability, but also satisfies the requirements of dynamic performance targets for controlling system.
Keywords�� spacecraft   servo mechanism   electromechanical actuator   drive and control   redundancy     
Received 2009-12-02;


About author: ½ ��(1973-),��,ɽ����ƽ��,��ʿ��,luhaocasc@sina.com.
½��, ���˻�, �����.ij�ͺ���������ʸ�������ŷ��������������[J]  �������պ����ѧѧ��, 2010,V36(12): 1417-1421
Lu Hao, Li Yunhua, Zhu Chenglin.Design theory of thrust vector control servo mechanism for a type of spacecraft[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2010,V36(12): 1417-1421
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