In this paper, the suppression of limit cycle oscillations due to the interaction of structure, inertia, and aerodynamics in a wing aeroelastic system in the presence of a combination of graded and sinusoidal gusts is explored. To estimate the wind gust that acts as a matched external disturbance to the wing aeroelastic system, a nonlinear disturbance observer is employed. By imposing bounds on trailing and leading edge deflection, a natural logarithmic (Ln) function–based attractor with a sliding mode control (SMC) scheme is formulated to offer pitch and plunge channel stabilization, and then the stability of LnSMC is confirmed by the Lyapunov criterion. To evaluate the effectiveness of the LnSMC technique, classical SMC and terminal SMC are put into action for comparison. However, outcomes from simulation and numerical analysis demonstrate that the LnSMC approach outperforms the other two referenced control techniques in terms of stabilization and convergence of the wing aeroelastic system.
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