Flight Optimization of Missile using Linear Matrix Inequality (LMI) Approach

The research entails a finite-element design of a 3d-autopilot missile synthesis of multiple objective controls by solving the inequalities encountered while using a linear matrix. The autopilot design analyses the performance methodologies for a group of finite models that are further linearised at different aerodynamic roll angles within the flight coverage for harnessing the uncertainties that are encountered confined within the high angle-of-attack region. Multiple simulation results are devised at various roll angle conditions to satisfy the performance of the controls.