Aeroelastic response of composite aircraft swept wings impacted by a laser beam

A closed-form solution for the thermoaeroelastic response of an aircraft swept wing made of advanced composite materials and exposed to a thermal impact generated by a laser beam is presented. For the aircraft wing, an advanced one-dimensional structural model that includes a number of nonclassical effects, such as transverse shear, warping inhibition, and thermoelastic anisotropy of constituent materials, is developed. It is supposed that the wing is immersed in an incompressible flowfield whose speed is below the flutter critical speed of the system. The solution of the problem has been obtained analytically in the space-time Laplace transform domain. Within this approach, the problem is reduced to the solution of an algebraic equation system in the transformed kinematical unknowns that is afterward inverted in the physical space. Although confined to the dynamic aeroelastic response, the approach of the dynamic response can provide important information on the conditions yielding the occurrence of the flutter instability.