Integrated Guidance and Control Design Subject to Actuator Saturation Based on Fully Actuated System Approach

Based on fully actuated system approach, this paper proposes a design scheme for integrated guidance and control systems subject to actuator saturation. By elimination elevation-order way, the integrated guidance and control model in the pitch channel is transformed into a high-order fully actuated system with uncertain disturbances and actuator saturation. Firstly, a disturbance observer is constructed to estimate the disturbances generated by model nonlinearities, unknown target maneuvers, variations of aerodynamic parameters, etc. Then, an observer-based fully actuated controller is designed to stabilize the integrated guidance and control system and perform disturbance attenuation. Since the missile’s deflection angle for pitch control is constrained by actuator saturation, an anti-windup compensator is introduced into the designed fully actuated controller to reduce the negative impact of saturation. Moreover, the stability conditions of the closed-loop system are established by the Lyapunov stability theory and the invariant set principle. Finally, a numerical simulation is provided to verify the effectiveness of the proposed design scheme.