To increase the range of re-entry flight and improve the performance of hypersonic gliding vehicle (HGV), a surrogate-assisted multidisciplinary design optimization (MDO) framework is developed in this paper. First, the HGV multidisciplinary optimization problem is defined to increase the range of re-entry flight subject to the constraints of overload, heat flux, aerodynamic pressure, and plot ratio. Then the parameterized geometry model is established based on the free form deformation method to effectively change the shape of HGV. The panel method is used to calculate the aerodynamic force and heat flux, where the heat flux in the stagnation region is obtained by the Detra-Kemp-Riddell formula. And the re-entry flight model is established considering the effect of oblateness perturbation and rotational angular velocity of Earth. Finally, the multidisciplinary optimization problem is efficiently solved by Kriging assisted constrained differential evolution (KRG-CDE) algorithm. After optimization, the flight range is increased by 34% while the heat flux in the stagnation region is decreased by 22%. Moreover, the optimization cost of KRG-CDE is reduced by 64% compared with that of the conventional differential algorithm, which illustrates the practicability and effectiveness of the proposed surrogate-assisted MDO framework.