Since the aerospace vehicle with the traditional fixed configuration cannot meet the requirements of the aerodynamic performance both at high and low speeds during the climbing section， a morphing adjustment strategy is proposed. Firstly， a morphing method with wing retraction is proposed， and an aerodynamic surrogate model with vehicle configuration variables is constructed. Secondly， the aerodynamic and trimming characteristics of the vehicle are analyzed based on the aerodynamic surrogate model. A morphing strategy is formulated based on the aerodynamic characteristics， and a center-of-mass position matching design is proposed based on the trimming characteristics. Thirdly， according to the constraints of the configuration variables and equilibrium state of climbing， the appropriate center-of-mass position is optimized with the objective of minimizing the control inputs， providing a reference for the design of the center-of-mass position of different configurations. Finally， the simulation results show that the morphing aerospace vehicle can share the load on the rudder surface and reduce the throttle during climbing missions， which increases the stability of the flight process.