Abstract
The question of active flutter control of an aeroelastic airfoil with leading- and trailing-edge control surfaces is investigated. The dynamical equations of a two-dimensional airfoil with polynomial nonlinearity in pitch are established. Then suppose that there are parametric uncertainties in both pitch stiffness and damping; Lyapunov function is used to design an adaptive control law of feedback linearization and a structured model reference adaptive control law. The simulation results and their analysis show preliminarily that: (1) the nonlinear controllers are effective for flutter suppression even if the control surface deflection is limited; (2) considering damping uncertainty has positive effect on reducing the convergence time but stiffness uncertainty plays the leading role for flutter control.
| Original language | English |
|---|---|
| Pages (from-to) | 775-780 |
| Number of pages | 6 |
| Journal | Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University |
| Volume | 33 |
| Issue number | 5 |
| State | Published - Oct 2015 |
Keywords
- Adaptive control system
- Airfoil
- Flutter
- Nonlinear aeroelasticity
- Parametric uncertainty