Abstract
AbstractThe objective of this paper is to describe a methodology to design control laws in the context of a computational aeroelasticity environment. The technical approach involves employing a systems identification technique to develop an explicit state‐space model for control law design from the output of a computational aeroelasticity code. As a control law design techniques, the standard LQG technique is employed. The computational aeroelasticity code is modified to accept control laws and perform closed‐loop simulations. Numerical results for flutter suppression of the BACT wind‐tunnel model are given. (© 2005 WILEY‐VCH Verlag GmbH & Co. KGaA, Weinheim)
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