Vibration and Aeroelasticity of Advanced Aircraft Wings Modeled as Thin-Walled Beams –Dynamics, Stability and Control

Within the basic framework of an existing anisotropic thin-walled beam model, a cou-ple of non-classical effects are further incorporated and the model thereby developed isvalidated. Three types of lay-up configurations, namely, the cross-ply, circumferentiallyuniform stiffness (CUS), and circumferentially asymmetric stiffness (CAS) are investi-gated. The solution methodology is based on the Extended Galerkin’s Method (EGM)and the non-classical effects on the static responses and natural frequencies are investi-gated. Comparisons of the predictions by the present model with the experimental dataand other analytical as well as numerical results are conducted and pertinent conclusionsare outlined. This work is the first attempt to validate a class of refined thin-walledbeam model that has been extensively used towards the study, among others, of dynamicresponse, static aeroelasticity and structural/aeroelastic feedback control.A slightly different version of this chapter has been submitted to the Journal of Composite Structuresfor publication