چكيده لاتين :
Flutter and limit cycle oscillations (LCO) control ofa structural
non-linear wing with actuator saturation is considered in this
paper. For this purpose composite nonlinear feedback (CNF)
theory is used. The CNF theory accounts for the effect of
actuator saturation and here it can be shown, this control
method can effectively suppress the flutter and LCO of a
structural nonlinear wing with constrained input. The
aeroelastic model is a low aspect ratio rectangular wing in a
low subsonic flow with structural nonlinearities. The structural
nonlinearity arises from double bending in both chord-wise and
span-wise directions (Von Karman plate theory). For
aerodynamics modelling a full and reduced order aerodynamics
model based on the modified vortex lattice method is used.
Results from simulations show, with this simple controller, we
can effectively suppress LCO and extendflutter boundary.
