LMI-Based H-Infinity Controller Design for Missile Guidance Control

In this study, a state-space model of a representative missile was developed to analyze its dynamic behavior under various input conditions. Using MATLAB simulations, the system’s responses to different control inputs were examined to understand the missile’s natural dynamics and response characteristics. Subsequently, an LMI-based H-infinity controller was designed to enhance the stability and performance of the missile guidance system. The controller was developed by formulating an optimization problem within the Linear Matrix Inequalities (LMI) framework, ensuring maximum stability and disturbance attenuation. The control design also incorporated input saturation constraints and reference tracking by augmenting the system with integral action. The designed controller was implemented and tested in MATLAB, and its effectiveness was evaluated based on system stability, disturbance attenuation. The LMI-based design approach allowed the control gains to be optimally determined, considering external disturbances. Simulation results demonstrate that the LMI-based H-infinity controller provides superior stability and improved disturbance attenuation. This study highlights that LMI-based optimization techniques can be effectively applied to missile guidance systems, offering a powerful tool for managing dynamic uncertainties and external disturbances.