Integrated guidance and control design for missile with terminal impact angle constraint based on sliding mode control  

作　　者：Peng Wu Ming Yang 

机构地区：[1]Control and Simulation Center, Harbin Institute of Technology, Harbin 150001, E R. China

出　　处：《Journal of Systems Engineering and Electronics》2010年第4期623-628,共6页系统工程与电子技术（英文版）

基　　金：supported by the Nationa Natural Science Foundation of China(60434010);Outstanding Youth Fund of Heilongjiang Province(JC200606)

摘　　要：Aimed at the guidance requirements of some missiles which attack targets with terminal impact angle at the terminal point,a new integrated guidance and control design scheme based on variable structure control approach for missile with terminal impact angle constraint is proposed.First,a mathematical model of an integrated guidance and control model in pitch plane is established,and then nonlinear transformation is employed to transform the mathematical model into a standard form suitable for sliding mode control method design.A sufficient condition for the existence of linear sliding surface is given in terms of linear matrix inequalities（LMIs）,based on which the corresponding reaching motion controller is also developed.To verify the effectiveness of the proposed integrated design scheme,the numerical simulation of missile is made.The simulation results demonstrate that the proposed guidance and control law can guide missile to hit the target with desired impact angle and desired flight attitude angle simultaneously.Aimed at the guidance requirements of some missiles which attack targets with terminal impact angle at the terminal point,a new integrated guidance and control design scheme based on variable structure control approach for missile with terminal impact angle constraint is proposed.First,a mathematical model of an integrated guidance and control model in pitch plane is established,and then nonlinear transformation is employed to transform the mathematical model into a standard form suitable for sliding mode control method design.A sufficient condition for the existence of linear sliding surface is given in terms of linear matrix inequalities（LMIs）,based on which the corresponding reaching motion controller is also developed.To verify the effectiveness of the proposed integrated design scheme,the numerical simulation of missile is made.The simulation results demonstrate that the proposed guidance and control law can guide missile to hit the target with desired impact angle and desired flight attitude angle simultaneously.

关 键 词：GUIDANCE terminal impact angle sliding mode control integrated guidance and control linear matrix inequality（LMI）. 

分 类 号：TP273[自动化与计算机技术—检测技术与自动化装置] E927[自动化与计算机技术—控制科学与工程]