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�������պ����ѧѧ�� 2007, Vol. 33 Issue (04) :397-400    DOI:
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����1, ����1, ������2*
1. �������պ����ѧ �ѧԺ, ���� 100083;
2. �й�����ƹ����Ź�˾, ���� 100830
Endoatmospheric interceptor fast response control using impulse attitude control motor
Wang Jin1, Chen Wanchun1, Yin Xingliang2*
1. School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;
2. China Aerospace Science & Industry Corp, Beijing 100830, China

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Abstract�� The effectiveness of aero control decreases as dynamic pressure decreases. Therefore impulse attitude control motor(ACM) is to be used to maintain fast response of missile in low dynamic pressure. A preliminary study of the method was given. The impact of ACM on the dynamics of missile was analyzed using assessment data. Then a control strategy was designed on the pitch plane after some simplifications. Aero-fin was used to counteract the aerodynamic moment so that the total aerodynamic moment would be zero and the attitude of missile would be mainly controlled by ACM. ACM control strategy was designed with the assumption that the increment of pitch angle was equal to the increment of angle of attack. Simulation results were given for step acceleration command which show that aero control is effective as ACM control in high dynamic pressure and ACM control becomes more effective than aero control as dynamic pressure decreases.
Keywords�� missile control   fast response   impulse attitude control motor     
Received 2006-05-10;
About author: �� ��(1981-),��,�Ĵ���Դ��,��ʿ��,99missile@sohu.com.
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����, ����, ������.�����������ص������˿ط���������Ӧ����[J]  �������պ����ѧѧ��, 2007,V33(04): 397-400
Wang Jin, Chen Wanchun, Yin Xingliang.Endoatmospheric interceptor fast response control using impulse attitude control motor[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2007,V33(04): 397-400
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http://bhxb.buaa.edu.cn//CN/     ��     http://bhxb.buaa.edu.cn//CN/Y2007/V33/I04/397
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