Abstract
Structural and aeroelastic tailoring applied to advanced straight and swept aircraft wings carrying external stores is addressed. The wing structure is modeled as a laminated composite plate exhibiting flexibility in transverse shear and warping restraint effects. The equations of motion and boundary conditions are obtained via Hamilton's variational principle and application of generalized function theory. For a comprehensive representation of the stores, their static weights and inertia terms are considered. Three-dimensional modified strip theory aerodynamics is employed, and the obtained eigenvalue/boundary value problems are solved using the extended Galerkin method. The model is used to investigate the implications of external stores and ply angle orientation on divergence, free vibration, and flutter. Within the context of aeroelastic tailoring, the influence of external stores attached to the wing structure has to be considered during the preliminary aircraft design phases.
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