Abstract: During high maneuvering flight conditions of modern advanced flight vehicles, the coupled motion of multi-degree-of-freedom would be induced. This behaviour presents the complex unsteady aerodynamic characteristics and multi-degree-of-freedom motion attitudes. A two-degree-of-freedom pitch/roll coupled motion test device, which could be used for investigating high angle of attack static test, pitch oscillation, pitch-up in high speed and pitch/roll coupled oscillation, has been established for investigating and evaluating multi-degree-of-freedom unsteady aerodynamic characteristics of advanced flight vehicles in FL-26 wind tunnel. The unsteady aerodynamic characteristics of one-degree-of-freedom motion and two-degree-of-freedom pitch/roll coupled oscillation for the typical 70-degree delta wing model are investigated based on the dynamic test devices. The results indicate that, the test data based on the dynamic test technique is reasonable and reliable which could represent the correct typical hysteresis characteristics of dynamic normal force and pitch moment. The test device is capable of measuring aerodynamic characteristics of two-degree-of-freedom pitch/roll coupled motion of advanced flight vehicles. This could provide technical support for the unsteady aerodynamic characteristics test evaluation and assessment of flight vehicles.