Integrated Guidance and Control of Homing Missiles Against Ground Fixed Targets

This paper presents a scheme of integrated guidance and autopilot design for homing missiles against ground fixed targets. An in- tegrated guidance and control model in the pitch plane is formulated and further changed into a normal form by nonlinear coordinate transformation. By adopting the sliding mode control approach, an adaptive nonlinear control law of the system is designed so that the missile can hit the target accurately with a desired impact attitude angle. The stability analysis of the closed-loop system is also con- ducted. The numerical simulation has confirmed the usefulness of the proposed design scheme.

作 者： Hou Mingzhe Duan Guangren   作者單位： Center for Control Theory and Guidance Technology, Harbin Institute of Technology, Harbin 150001, China  刊 名： 中國航空學報（英文版）  ISTIC 英文刊名： CHINESE JOURNAL OF AERONAUTICS  年，卷(期)： 2008 21(2)  分類號： V2  關鍵詞： integrated guidance and control   pitch plane   ground fixed target   nonlinear   adaptive  

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