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.
Aeroelastic vibration feedback control of smart aircraft wings in subsonic flight speeds
Smart Structures and Materials 2002: Smart Structures and Integrated Systems ; 2002 ; San Diego,California,United States
Proc. SPIE ; 4701
2002-07-15
Conference paper
Electronic Resource
English