Dynamic Stability Analysis of Aircraft Landing Gear using PID Controller

Abstract

In the aviation industry, ensuring both the structural integrity and passenger comfort of aircraft stands as a primary concern, driven by the potential hazards posed by fatigue failures in structural components. This study endeavours to undertake a comparative examination of various damping coefficients and spring constants within a typical landing gear system. These parameters are then integrated with a Proportional-Integral-Derivative (PID) controller to elevate the performance standards of the landing gear control system. The overarching objectives include the reduction of peak overshoot and the minimization of settling time concerning aircraft displacement, thereby amplifying overall safety measures and passenger comfort levels. The landing gear system under investigation is delineated through a sophisticated (2 DOF) Mass-Spring-Damper model, which furnishes the foundation for deriving the equation of motion. Leveraging the specific parameters of the aircraft, alongside the derived equations, a meticulously crafted MATLAB/Simulink model is established, facilitating comprehensive analysis and simulation procedures. By applying Laplace transform methodologies, a transfer function is meticulously constructed. This facilitates the seamless integration of a PID controller with the system, thereby laying the groundwork for establishing a closed-loop control system. Such a system affords precise regulation and optimization of the landing gear dynamics, culminating in enhanced operational efficacy. A rigorous comparative analysis is conducted to gauge the efficacy of various models, prompting adjustments to the spring constants and damping coefficients based on the discerned findings. This iterative refinement process serves to fine-tune and optimize the system's performance in alignment with the predefined objectives.