Akademik Veri Yönetim Sistemi
The Eurasia Proceedings of Science, Technology,Engineering & Mathematics (EPSTEM), cilt.33, ss.1-19, 2025 (Scopus)
In this study, a state-space model of a representative missile was developed to analyze its dynamicbehavior under various input conditions. Using MATLAB simulations, the system’s responses to different controlinputs 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 guidancesystem. The controller was developed by formulating an optimization problem within the Linear MatrixInequalities (LMI) framework, ensuring maximum stability and disturbance attenuation. The control design alsoincorporated 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 onsystem stability, disturbance attenuation. The LMI-based design approach allowed the control gains to beoptimally determined, considering external disturbances. Simulation results demonstrate that the LMI-based H-infinity controller provides superior stability and improved disturbance attenuation. This study highlights thatLMI-based optimization techniques can be effectively applied to missile guidance systems, offering a powerfultool for managing dynamic uncertainties and external disturbances.