Design of LQR Control Law for AIRCRAFT Longitudinal Dynamics Using SIMULINK Model Architecture

This presents a SIMULINK model architecture designed for aircraft longitudinal equations using Linear Quadratic Regulator (LQR) control law, suitable for aircraft control and simulation applications. The LQR control methodology is a widely-adopted optimal control technique that minimizes a quadratic cost function by weighting system states and control inputs. The implementation typically involves solving the algebraic Riccati equation to obtain optimal feedback gain matrices. SIMULINK serves as a powerful simulation environment that enables engineers to efficiently construct, debug, and validate dynamic system models through graphical block diagram interfaces. Key functional components include state-space representations of aircraft longitudinal dynamics, LQR controller blocks with configurable weighting matrices, and signal routing for elevator deflection and pitch angle control. This model architecture holds significant value for research and practical applications in aircraft control systems, providing a framework for stability analysis, controller tuning, and real-time simulation validation.