15 July 2002 Aeroelastic vibration feedback control of smart aircraft wings in subsonic flight speeds
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Abstract
A minimax control design aimed at augmenting the flutter envelope and enhancing the dynamic aeroelastic response of a smart aircraft wing subject to gust/blast loads is presented. The smart aircraft wing is modeled as an anisotropic thin-walled beam featuring circumferentially asymmetric stiffness lay-up and a number of non-classical effects such as transverse shear, warping restraint and 3-D strain effects. Adaptive materials technology is used for implementing the active control via the boundary bending moment feedback mechanism. The unsteady aerodynamic loads in subsonic compressible flows are based on 2-D indicial functions considered in conjunction with aerodynamic strip theory extended to 3-D wing model. The capability of control on flutter suppression and dynamic response enhancement are investigated, the corresponding applied voltage requirement and power consumption are addressed.
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Zhanming Qin, Liviu I. Librescu, "Aeroelastic vibration feedback control of smart aircraft wings in subsonic flight speeds", Proc. SPIE 4701, Smart Structures and Materials 2002: Smart Structures and Integrated Systems, (15 July 2002); doi: 10.1117/12.474699; https://doi.org/10.1117/12.474699
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