大气层内导弹姿态控制方法研究

本文以大气层内导弹为研究对象,对导弹的姿态控制方法进行研究.根据大气层内导弹运动方程组及空气动力方程等得出导弹的姿态控制系统数学模型.由于导弹的姿态控制数学模型是强耦合、非线性的,因而在控制器设计之前,采用小扰动理论进行线性化处理,得到俯仰、偏航、滚转三个通道的传递函数.针对特征点,采用PD控制方法分别设计三通道的控制律,在此基础上,进一步设计了基于增益调度的PD控制规律.仿真结果表明,提出的姿态控制方法可以实现大气层内导弹的姿态控制,满足指标要求.

Research on the Attitude Control Methods of Missile within the Atmosphere

In this paper, we do some research on the attitude control methods for missile within the atmosphere. According to the equations of motion in the atmosphere and aerodynamic equations ,we get the mathematical model of the attitude control system. As the mathematical model is strongly coupled, nonlinear, and thus before the controller is designed, we get the transfer functions of the pitch, yaw and roll channels based on the small perturbation linearization theory. For single feature point, using the PD control method designed control law of the three channels respectively, on this basis, PD control law based on gain scheduling is further designed. Simulation results show that the proposed method for attitude control work well and meet the performance requirements.