Abstract: An integrated optimization methodology is developed for the design of strut location and structure for composite strut-braced wing. The optimization design with consideration of aeroelastic effects and uncertainties of composite plies is conducted in the case of two critical design load conditons. The objective is to minimize the structural mass subject to the constraints of vertical deformation and torsion angle at wingtip, global buckling of strut, flutter speed and stress. The synchronized optimization and the robust optimization are both accomplished for the location and structural parameters in one optimization process. The results indicate that the strut location can be significantly influenced by the constraints of vertical deformation at wingtip and flutter speed. The optimal spanwise locations of strut are close to the wingroot area, and the global buckling of strut will be the critical constraint for synchronized optimization design. The capacity of resisting disturbance is excellent for the robust optimal combination of strut location and structural parameters in case of the uncertain perturbation of composite plies. The optimal strut location resulted from robust design will change with the perturbation ranges of design variables, and the vertical displacement at wingtip will be the critical constraint for robust optimization design.