Analysis of Active Flutter Suppression With Leading- and Trailing-Edge Control Surfaces Via Gm-Method

Document Number: 2005-01-3421

Date Published: October 2005

Author(s):
Ying Teng - The Boeing Company
Hsin-Piao Chen - California State University at Long Beach

Abstract:
The robust stability of an active wing section with leading- and trailing-edge control surfaces is investigated using \gm-method. Mathematical models and implementation issues of active flutter suppression are described. The multi-input/multi-output aeroservoelastic systems and algorithms are developed by \gm-control law to account for the uncertainty parameters/perturbations associated with the unsteady dynamic pressure, the variable structural damping and the nonlinear structural stiffness. The nominal and robust stability margins, modal properties, critical flutter airspeeds and frequencies are computed to predict the flutter of the aeroelastic system and to investigate the aeroservoelastic stability in \gm-framework. The simulation results are presented for the comparisons among: a) the uncontrolled wing section, b) the active wing section with a single trailing-edge flap controller (K1) activated, and, c) the one with both the leading- and trailing-edge flap controllers (K2 and K1) activated to demonstrate the improved effectiveness for flutter suppression by using two control surfaces.

File Size: 1054K
Product Status: In Stock

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