In this paper, iterative methods are used to investigate the static aeroelastic of high aspect ratio wings. The aerodynamic loads of wings are calulated by the vortex-lattice method, and the structural characteristics of wings are obtained by the Numerical simulation of the software(ANSYS), and then interpolate the aerodynamic loads into the finite element calculation grid node to exchange data by the surface spline interpolation method. Take airborne dispenser as an illustration, wing-body connected mode is simplified during calculation, the results show wing deformation and pressure distributions before deformation and after, in which elasticity is considered, wing deformational characteristic and pressure distributions of different materials are also compared.