Due to the large flutter boundary variation and the difficulty of conducting flutter tests on the ground of hyper-sonic vehicles，the thermal flutter test technology of wing surface structure on the ground is studied. Firstly， the aerodynamic heating of the structure is analyzed based on the engineering method， and then the thermal flutter characteristics of the structure are evaluated. Considering the influence of structure temperature rise on the actual flight， an aerodynamic force comprehensive optimization order reduction algorithm based on multi-condition points is established to ensure the accuracy of aerodynamic force simulation during the whole temperature rise process. By establishing a multi-point coordinated control system based on the fuzzy logic proportional integral derivative（PID） control， the excitation force controller of the time-varying system in the process of temperature rise is designed. Finally， the ground flutter test system is built， and the thermal flutter characteristics of the structure are tested according to the typical flight conditions. The relative error between the test results and the simulation results is about 10%.