Aircraft nose landing gear shimmy, categorized as self-excited lateral and torsional vibrations, poses a significant risk of instability at high speeds, potentially leading to catastrophic consequences. Effective suppression of these vibrations is therefore crucial. This study presents the design and implementation of a Takagi–Sugeno fuzzy logic controller for mitigating nose landing gear shimmy. The performance of the proposed controller is evaluated through simulations conducted in the MATLAB/Simulink environment. Its efficacy is verified and compared against an optimal State-Dependent Riccati Equation (SDRE) controller, alongside the Robust Computed Torque Method (RCTM) and an adaptive controller. The results demonstrate a substantial improvement in closed-loop system performance and a significant reduction in shimmy vibrations.
khale et al. (Wed,) studied this question.