Aircraft Pitch Control Via Parametric Identification and PID Optimization

A comprehensive methodology for designing an aircraft pitch angle control system is proposed, combining mathematical modeling, aerodynamic parameter identification, and controller optimization. A comparative study was conducted on the accuracy of the Euler and 4th-order Runge-Kutta methods for numerical integration of longitudinal short period motion equations in identification tasks. It was established that the Runge-Kutta method provides higher accuracy for estimating aerodynamic force coefficients, while the Euler method is preferable for moment analysis, defining the criteria for algorithm selection during data generation. Automated tuning of the PID controller in Simulink achieved record dynamic system performance characteristics (without considering the actuator): rise time - 0.0709 s, overshoot - 11.6%, which is 20-30% superior to results from known counterparts. The developed approach demonstrates the possibility of replacing labor-intensive flight tests with digital models while maintaining accuracy, thereby reducing design time. The results confirm that the integration of numerical modeling, parametric identification, and optimization forms a new standard for preliminary studies in aviation technology, aligning with the digitalization trends in the aerospace industry.