Generalized composite noncertainty-equivalence adaptive control of a prototypical wing section with torsional nonlinearity

The paper presents a generalized composite noncertainty-equivalence adaptive control system for the of prototypical aeroelastic wing section using single trailing-edge surface. plunge–pitch (two-degree-of-freedom) dynamics this include torsional pitch-axis nonlinearity. open-loop exhibits limit cycle oscillations beyond critical free-stream velocity. It is assumed that parameters model are not known. objective to suppress oscillatory responses system. Based on immersion and invariance approach, (NCEA) regulation pitch angle designed. consists module parameter identifier—designed independently. integral estimation law based (1) (I&I) theory, (2) gradient-based adaptation algorithm, (3) classical certainty-equivalence (CEA) update rule. Besides component, full estimate also includes judiciously chosen nonlinear algebraic function. This identifier inherits stronger stability properties. Using Lyapunov analysis, asymptotic suppression boundedness trajectories established. Interestingly, in closed-loop including rule, there exist two attractive manifolds which system’s converge. Simulation results presented show plunge displacement despite uncertainties parameters. Furthermore, performance properties NCEA system—including rule CEA system—are better than simple