针对鸭式布局导弹静不稳定控制的问题进行研究。首先根据导弹动力学模型建立了弹体纵向平面运动方程,基于小扰动线性化方法及拉普拉斯变换方法得到了动力学系数及弹体传递函数。然后分别采用伪攻角三回路过载自动驾驶仪的线性控制方法及Backstepping的非线性控制方法进行了静不稳定导弹控制系统设计。使用过载阶跃指令输入进行了仿真,并对两种方法的设计原理与仿真结果进行了对比。结果表明,采用三回路过载自动驾驶仪的线性控制方法及采用Backstepping的非线性控制方法均可对鸭式布局静不稳定导弹进行控制,舵偏角需先打负偏角,然后再打正偏角直至最后稳定到某一舵偏角。非线性控制方法设计简单,所需控制参数较少,并具有更快的响应速度及更小的控制量需求,对控制系统性能提升具有良好的作用和意义。

Aiming at the problem of control the relaxed stable stability canard missile.First of all,the longitudinal plane motion equations for the missile were established according to the Dynamic model,and the missile dynamic coefficients and missile body transfer function of the missile were obtained using the small perturbation linearization method and Laplace transform method.Then,the linear control method of pseudo-angle of attack three-loop overload autopilot and the nonlinear control method of Backstepping were respectively used to design the relaxed stable stability missile control system.Simulation is carried out with overload step instruction input,the design principles and simulation results of the two methods were both compared.The results show that the linear control method of the pseudo-angle of attack three-loop overload autopilot and the nonlinear control method of Backstepping can both control the relaxed stable stability canard missile.The rudder deflection of angle needs to be deflected first in the negative direction,and then in the positive direction until it is finally stabilized at a certain rudder deflection of angle.It can be seen that the nonlinear control method is simple in design,requires fewer control parameters,and has faster response speed,smaller control demand,which has a good effect and significance for improving the performance of control system.