ON THE STATIC AEROELASTIC TAILORING OF COMPOSITE AIRCRAFT SWEPT WINGS MODELED AS THIN-WALLED BEAM STRUCTURES

The sub-critical static aeroelastic response and the divergence instability of swept-forward aircraft wing structures constructed of anisotropic composite materials is analyzed. The new element distinguishing this study from the previous, existing ones is the structural model in which framework this problem is treated. In this sense, in contrast to the classical plate-beam or solid-beam models traditionally used in the study of these problems, the thin-walled anisotropic composite beam model is adopted here. The model used incorporates a number of non-classical effects. Among these are the anisotropy of the material of the constituent layers, the transverse shear deformation and the primary and secondary warping effects. Within the framework of this study, in addition to an assessment of the influence of the previously mentioned effects, the aeroelastic tailoring technique is applied and as a result, a series of conclusions concerning the enhancement of the static aeroelastic response characteristics of aeronautical wing structures made of advanced composite materials are outlined.