Optimal Flutter Suppression of Nonlinear Typical Wing Section Using Time-Domain Finite Elements Method
Publication: Journal of Aerospace Engineering
Volume 27, Issue 5
Abstract
In this paper, the optimal time-domain finite element method is applied to the flutter suppression of a nonlinear two-dimensional typical wing section. The aeroelastic governing equations are based on the inclusion of stiffness nonlinearity in pitching motion and on the quasi-steady aerodynamics. The flutter suppression problem is formulated as a general optimization problem with equality constraints that are functions of state variables. Using the variational approach, the optimality conditions are derived and the resulting equations are discretized in time-domain. Then, by setting out the discrete equations, a set of nonlinear algebraic equations is generated, and through the Newton–Raphson method, the optimum answer is attained. The numerical results are presented in which the performance of the nonlinear optimal control system designed by the time-domain finite element technique for nonlinear aeroelastic wing sections is illustrated.
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Published In
Journal of Aerospace Engineering
Volume 27 • Issue 5 • September 2014
Copyright
© 2014 American Society of Civil Engineers.
History
Received: Jan 14, 2012
Accepted: Mar 19, 2013
Published online: Mar 20, 2013
Published in print: Sep 1, 2014
Discussion open until: Oct 15, 2014
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