μ-Method for Robust Stability of Active Aeroelastic Wing with Multiple Control Surfaces

摘要

μ-method for robust stability of an active aeroelastic wing section with leading and tailing edge control surface is developed. Robust system is constructed to account for the uncertainty parameters associated with the variable structural damping and the nonlinear structural stiffness. The nominal and robust stability margins, critical flutter airspeeds and frequencies are computed to analyze the aeroelastic and aeroservoelastic robust stability in the μ-framework. The analysis process shows μ method for robust stability analysis of aeroservoelastic system with uncertainties is effective. The simulation results indicated that uncertain perturbation reduces stability margin of system. The aeroservoelastic system increases flutter speed and critical dynamic pressure to the aeroelastic (openloop) system, specifically increases in flutter speed is 12 % when leading edge flap activated and 32 % when both leading and trailing edge flap activated. The system tends to stabilize more quickly and trailing edge flap deflects smaller by using both the leading and trailing edge control surfaces simultaneously.