Missile roll and acceleration autopilot design based on linear active disturbance rejection control

In this paper, a linear active disturbance rejection controller is proposed for roll and acceleration autopilot control of nonlinear missile systems to address the presence of disturbances due to unknown system parameters. The controller design uses the linearized roll and normal acceleration models of a six-degree-of-freedom missile model. The linear extended state observer is then applied to the linearized model to estimate and compensate for the disturbances. In the roll channel, a second-order controller is applied to stabilize the roll and decouple the pitch and yaw channels. A double-loop acceleration controller is applied to the pitch and yaw channels. Several comparative simulations demonstrate the effectiveness of the proposed method. The simulation results showed that the proposed controller exhibits better control performance in both simple and extreme maneuvers while requiring fewer system parameters.