<p>This paper presents a framework for aeroelastic modeling of flexible wings with trailing edge morphing using an intermediate kinematic mesh. The approach targets morphing concepts with sufficiently stiff actuation, where the prescribed actuator displacement defines the airfoil shape and can withstand aerodynamic loads, enabling a simplified structural representation. The wing structure is modeled using linear Euler-Bernoulli beam elements, while unsteady aerodynamics are modeled using the unsteady vortex lattice method (UVLM). The actively controlled kinematic mesh prescribes the morphing geometry and transfers both structural deformations and morphing-induced displacements to the aerodynamic mesh, while mapping aerodynamic loads back to the beam model. This coupling enables smooth geometry and load transfer using thin-plate spline interpolation and modified inverse distance weighting interpolation. The modeling framework is validated against analytical reference based on the Wagner unsteady aerodynamic model, and the modified inverse-distance weighting load transfer is shown to conserve the total torsional moment. The framework is demonstrated on a representative wing with morphing identified from an active rib demonstrator, and several spanwise morphing cases are investigated. The low number of model parameters and the morphing description through a single prescribed function makes the framework particularly suited for iterative parametric studies and control-oriented analysis of aeroelastic response of morphing wings.</p>