Adaptive Controller Design for the Air-to-Air Missile Uncertain System

Yanjun Liang, Junqi Liang, Zhongsheng Wang

The guidance and control problem of the air-to-air missile system is studied. A nonlinear, coupling dynamic model of the air-to-air missile with six degrees of freedom is investigated, and an uncertain control system is proposed according to some assumptions and simplifications. In order to make the closed loop of the air-to-air missile control system globally uniformly asymptotic stable and the output of the closed loop control system  asymptotically approach zero, based on adaptive control theory, an adaptive control law for uncertain parameters and a controller for the air-to-air missile are designed. Numerical simulations show that the control system proves the correctness and has preferably tracking performance and illustrate the effectiveness of the proposed controller.