Guidance Law Design Under Impact Angle Constraint Based on Nussbaum-type Gain Technique

作     者：郭建国 周军 

作者机构：Institute of Precision Guidance and ControlNorthwestern Polytechnical University 

出 版 物：《Defence Technology（防务技术）》 (Defence Technology)

年 卷 期：2010年第6卷第4期

页      面：253-257页

学科分类：08[工学] 081105[工学-导航、制导与控制] 0811[工学-控制科学与工程] 

基　　金：Sponsored by Fundamental Science Foundation Grant of Northwestern Polytechnical University(JC201024) 

主　　题：control and navigation technology of aerocraft stability guidance law impact angle adaptive control 

摘      要：Aiming at the guidance problem under impact angle constraint for homing missile against ground targets,a new adaptive robust nonlinear terminal guidance law was proposed in this *** to nonlinear kinetic relationship between the missile and target in vertical plane,a mathematic model was formulated while the motion of target and the system structure perturbation were regarded as limited *** on the ideas of zeroing the rate of line-of-sight(LOS)angle and the impact angular tracking error,a nonlinear control strategy was contrived to obtain adaptive robust guidance law by adopting Nussbaum-type gain technique under a desired impact *** stability of guidance system in finite time is strictly proven by using Lyapunov stability ***,the numerical simulation verifies the effectiveness of the proposed scheme.