Aeroelastic vibration feedback control of smart aircraft wings in subsonic flight speeds

Zhanming Qin; Liviu I. Librescu

doi:10.1117/12.474699

15 July 2002 Aeroelastic vibration feedback control of smart aircraft wings in subsonic flight speeds

Zhanming Qin, Liviu I. Librescu

Proceedings Volume 4701, Smart Structures and Materials 2002: Smart Structures and Integrated Systems; (2002) https://doi.org/10.1117/12.474699
Event: SPIE's 9th Annual International Symposium on Smart Structures and Materials, 2002, San Diego, California, United States

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.

Citation Download Citation

Zhanming Qin and 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); https://doi.org/10.1117/12.474699

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