The characteristics of channel interaction and coupling angle were deduced by the transfer function coupling with space phase caused by servo rolling; Magnus and Gyro effects were discussed separately according to their different dynamic characteristics. The deviation of the response moment angle of missile under the stable state conditions was obtained. The command compensation of the deflection angle of control moment was carried out, and the expected result was obtained. The study indicates that the Gyro effect can be weakened by appending the propriety damping loop, and more satisfied characteristic can be obtained with stable state decoupling.
Key words
rolling missile /
coupling /
space phase
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References
[1]张有济. 战术导弹飞行力学设计[M]. 北京:中国宇航出版社,1996. ZHANG You ji. Tactical missile flight mechanics design[M]. Beijing: China Astronautics Publishing House,1996.(in Chinese)
[2]万春熙. 反坦克导弹设计原理[M]. 北京:国防工业出版社,1981. WAN Chun xi. Principles of anti tank design[M]. Beijing: National Defense Industry Press, 1981.(in Chinese)
[3]袁天宝,刘新建,秦子增.自旋弹道导弹动力学与控制[J]. 宇航学报,2006,(3):217-221. YUAN Tian bao, LIU Xin jian, QIN Zi zeng. Dynamic and control of spinning ballistic missile[J]. Journal of Astronautics, 2006,(3): 217-221.(in Chinese)
[4]钱杏芳,林瑞雄,赵亚男. 导弹飞行力学[M]. 北京理工大学出版社,2000. QIAN Xing fang, LIN Rui xiong, ZHAO Ya nan. Missile flight mechanics[M]. Beijing: Beijing Institute of Technology Press, 2000.(in Chinese)
[5]德米特里耶夫斯基 A A, 雷申科 Л Н, 波哥吉斯托夫 C C. 外弹道学[M]. 韩子鹏,译. 北京:国防工业出版社,2000. ДМИТРИЕВСКИЙ A A, ДЪГСЕНКО Д Н, БОГОДИСТОВ C C. Exterior ballistics[M]. Beijing: National Defense Industry Preess, 2000.(in Chinese)
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Footnotes
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