Bifurcation control of aeroelastic limit cycle oscillations
An active flutter suppression using linear saturated control is investigated for a 2dof wing section with nonlinear torsional stiffness and limited deflection amplitude of its single control effector. The suppression of limit cycle oscillations in the nonlinear closed-loop system is achieved through maximization of the stability region of the linearized system. A bifurcation sequence leading to limit cycle disappearance is revealed. With increase of the maximum control input amplitude, the closed-loop limit cycle is transformed into a stable torus, which disappears at higher control amplitude through a nonlocal bifurcation similar to a boundary crisis in chaotic systems. Finally, a saddle-node bifurcation of the limit cycle gives necessary conditions for global stability in the closed-loop system.
Citation : Demenkov, M. and Goman, M. (2009) Bifurcation control of aeroelastic limit cycle oscillations. The Second IFAC meeting on Analysis and Control of Chaotic Systems, 2 (1), pp. 355-360
Research Group : Centre for Engineering Science and Advanced Systems
Peer Reviewed : Yes