战术导弹的自适应飞行控制方案的研究

THE STUDY ON THE ADAPTIVE FLIGHT CONTROL SCHEME OF TACTICAL MISSILE

在对现有某型地空导弹飞行控制系统进行全面仿真分析的基础上,根据新的性能指标要求,应用模型参考自适应控制理论及李雅普诺夫方法,选定了自适应参数,完成了方案设计,并通过全弹道飞行仿真,对该方案进行了初步论证。论证结果表明,新型系统比原系统有很大改进,可满足高、中、低不同高度的弹道性能指标,且具有较好的抗干扰能力,为新型导弹武器系统设计提供了科学依据。

In this paper, the adaptive control law was devised and the new scheme was designed, by the result of simulation analysis for certain ground-to-air missile flight control system and requirement of the characteristic index of the new control system and using theory of model reference adaptive control. The scheme was primarily proven by means of the entire and detailed simulation research on the entire trajectory. It is compared with original system so that primarily satisfies the needs of the performance index of the hight, middle and low trajectory and posses certain anti—inter—ference ability. Thus it provides important scientific base for design of the new missile weapon system.