文献类型：期刊文章

作　　者：侯明哲[1] 段广仁[1]

机构地区：[1]哈尔滨工业大学控制理论与制导技术研究中心,黑龙江哈尔滨150001

出　　处：《Chinese Journal of Aeronautics》

基　　金：Major Program of National Natural Science Founda-tion of China (60710002);Program for Changjiang Scholars and Innovative Research Team in University

年　　份：2008

卷　　号：21

期　　号：2

起止页码：162-168

语　　种：中文

收录情况：AJ、AMR、CAS、CSA、CSA-PROQEUST、CSCD、CSCD2011_2012、DOAJ、EBSCO、EI(收录号：20081911242102)、IC、INSPEC、JST、SCI(收录号：WOS:000255384000009)、SCI-EXPANDED(收录号：WOS:000255384000009)、SCIE、SCOPUS、WOS、ZGKJHX、普通刊

摘　　要：This paper presents a scheme of integrated guidance and autopilot design for homing missiles against ground fixed targets. An integrated 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 conducted. The numerical simulation has confirmed the usefulness of the proposed design scheme.

关 键 词：integrated guidance and control  pitch plane  ground fixed target  nonlinear  adaptive  

分 类 号：TJ765]