In order to study the effects of wing mounted stores upon the aeroelasticity of advanced aircraft wings, a comprehensive structural model has been developed. The wing structure is idealized as a laminated composite plate thus leading to the concept of a shear deformable plate-beam model. Free body motions at the wing root are induced by the motion of the airframe in pitching, plunging, and rolling. Non-classical effects like warping inhibition and transverse shear flexibility are included in the structural model. The relevant equations of motion as well as the appropriate boundary conditions are obtained via Hamilton’s variational principle and application of generalized function theory in order to exactly consider the spanwise location and properties of the attached stores. Numerical predictions for divergence behavior and static aeroelastic response of the system using extended Galerkin’s Method are supplied.