LIMIT CYCLE OSCILLATIONS CONTROL OF A NONLINEAR WING IN A LOW SUBSONIC FLOW

Limit cycle oscillation (LCO) control of a low aspectratio rectangular wing in low subsonic flow isconsidered here. The nonlinear structural model is basedon Von Karman plate theory that can model doublebending in both chord-wise and span-wise directions.For aerodynamic modeling, a vortex latticeaerodynamic method is used. A simple controller basedon optimal linear quadratic regulator combined withlinear reduced order observer is used for vibration suppression of this highly nonlinear system. Resultsshow that, proposed controller can effectively controllimit cycle oscillations.

کلیدواژه ها:

LCO Control ، Von Karman Plate ، NonlinearAero-elasticity ، Flutter ، Nonlinear Wing ، Aero-elastic Instability