Modeling and Dynamic Analysis of Pitch Motion Control of an Aircraft System

الملخص

Safe and efficient flight operations require accurate and steady aircraft pitch angle control. Conventional control approaches struggle to achieve ideal transient response characteristics like minimum overshoot and fast settling time. This thesis compares aircraft pitch angle control techniques. Due to its instability, the open-loop aircraft pitch system requires powerful feedback control. This paper simulates the longitudinal dynamics of an aircraft pitch control system and builds PID controllers utilizing Trial-and-Error, Ziegler-Nichols, and GA-based optimization. A Model Predictive Control (MPC) technique is also tested. While Trial-and-Error and Ziegler-Nichols conventional PID tuning approaches stabilize the system, simulation studies show that they have higher overshoot and longer settling periods in transient response. The GA-optimized PID controller has a faster reaction (0.204 s, peak time 0.619 s, settling time 1.25 s) and a 5.79% reduction in overshoot. With comparable performance measures (settling time of 1.33 s, overshoot of 6.11%), the MPC technique works well in complex control contexts. A thorough comparison shows that the GA-tuned PID controller beats classical PID approaches and MPC in important transient response characteristics. This shows that artificial intelligence can optimize aircraft pitch control systems better. The results show that GA-based tuning can provide accurate and robust control, providing insights for aerospace control system design.