NONCLASSICAL EFFECTS ON DIVERGENCE AND FLUTTER OF ANISOTROPIC SWEPT AIRCRAFT WINGS

A refined structural model of swept aircraft wings is presented and us ed to study the associated flutter and divergence instability in an in compressible gas Row. The structural model incorporates nonclassical e ffects such as anisotropy, heterogeneity, transverse shear, and warpin g inhibition. An exact solution methodology appropriate for parametric studies is wed to specifically determine the effects of transverse sh ear and warping restraint on aeroelastic instabilities. The results re veal strong quantitative and qualitative Implications for instability predictions. The solution methodology yields results that are in excel lent agreement with an exact approach devised for a special case and p rovides a high-efficiency mathematical tool for dealing with flutter a nd divergence instability problems.