The variable structure autopilot of some middle-ranged air intercept missile ( AIM ) is designed according to model reference variable structure terminal sliding mode control scheme. 应用模型参考变结构最终滑态控制方案设计了某型中距拦射空空导弹变结构自动驾驶仪。
For dealing with the nonlinearity and meeting the response time requirement of air defense intercept missile system with side jets, the design of aerodynamic and side-jet compound control law using gain scheduling method is investigated. 本文主要针对大气层内带有侧向喷流装置的防空拦截导弹系统的强非线性特性与快速性响应要求,基于增益调度方法对复合控制律进行设计。