Aircraft Control System Design using Linear Inequality Approach

I have developed an aircraft control system design code based on linear inequality methodology. This approach offers significant advantages including strong feasibility and rapid computational performance, though it requires substantial mathematical foundation. The implementation involves formulating control constraints as linear inequalities and solving them using MATLAB's optimization toolbox functions such as linprog(). To enhance code usability, I have performed comprehensive optimization and added detailed inline comments explaining key algorithmic steps like constraint formulation, solution convergence checks, and stability margin calculations. Users should first review the accompanying m-file documentation, which describes function interfaces, input parameter requirements, and output variable structures. For validation purposes, I created a Simulink model that interfaces with the core algorithm to simulate aircraft dynamics. The simulation tests demonstrate that this control system achieves high precision and robust stability, effectively handling various flight conditions through proper gain scheduling and disturbance rejection mechanisms.