摘要
针对传统制导与控制系统分开设计在拦截高速机动目标时的缺陷,提出一种高阶滑模制导控制一体化方法。综合考虑弹目拦截几何与导弹动态,根据零化视线(LOS)角速率的准则,将导弹制导控制问题转化为一个三阶积分链系统的镇定问题。基于几何齐次理论设计了标称系统的全局有限时间镇定控制律,同时针对目标机动和导弹气动参数摄动等带来的不确定性,利用超扭曲算法(STA)设计了补偿控制律。仿真结果表明,与传统制导与控制系统分开设计相比,本文所提出的鲁棒高阶滑模制导控制一体化方法具有更小的脱靶量,且导弹姿态和控制舵偏角的变化更加平缓。
Aiming at the disadvantages of traditional two-loop guidance and control system against high speed and maneu- verable targets, an integrated sliding mode guidance and control is derived in this paper. Through combining the intercept geometry with missile dynamics and basing on the principle of zeroing the line of sight （LOS） rate, a guidance and control problem is transformed to that of stabilization of a third integral chain system. Based on geometric homogeneity, a global fi- nite-time stabilization control law for nominal systems is proposed. For the uncertainty of the system caused by target maneu- verability and missile aerodynamic parameter perturbation, a compensating control law is provided using the super twisting algorithm （STA）. Simulation results show that the proposed integrated guidance and control algorithm possesses the advan- tages of smaller miss distance and smoother variations in missile attitude and elevators over the conventional two-loop de- sign.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2013年第9期2212-2218,共7页
Acta Aeronautica et Astronautica Sinica
基金
航空科学基金(20110196005)~~
关键词
导弹
制导控制一体化
高阶滑模
几何齐次理论
超扭曲算法
missiles integrated guidance and control high order sliding mode geometric homogeneity theory super twis-ting algorithm
