Missile autopilots for aerodynamic angle control and acceleration control are designed for fin-controlled missiles during the boost phase. In the boost phase, the speed change and the parameter variation of the missile are fast and large. To deal with the time-varying characteristics of the missile, the time-varying parameters are considered in nonlinear dynamics, and the parametric uncertainties are modeled. A state-feedback controller is designed for aerodynamic angle control based on a robust-backstepping scheme. Also, an output feedback controller is designed for acceleration control, where the acceleration dynamics are derived using input–output linearization. Numerical simulations are performed to demonstrate the performance of the proposed controllers.

中文翻译：

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考虑时变参数和不确定性的鲁棒反步导弹自动驾驶仪设计

用于气动角度控制和加速度控制的导弹自动驾驶仪是为助推阶段的尾翼控制导弹设计的。在助推阶段，导弹的速度变化和参数变化快且大。针对导弹的时变特性，在非线性动力学中考虑了时变参数，并对参数不确定性进行了建模。状态反馈控制器设计用于基于鲁棒反步方案的气动角度控制。此外，还设计了一个输出反馈控制器用于加速度控制，其中加速度动态是使用输入-输出线性化得出的。进行数值模拟以证明所提出的控制器的性能。