Abstract: In order to research dynamic derivatives of large transport aircraft, advanced fighter aircraft, propulsion and airframe integration aircraft in high speed wind tunnels, a dynamic derivative test technique based on the small amplitude forced-oscillation test principle has been developed in the 2 meter scale high speed wind tunnels(FL-26 and FL-28) of China Aerodynamics Research & Development Center. In this paper, the composition of the system is introduced, and some key techniques in the development of the system are emphasized. Firstly, high strength, good rigidity of aviation lightweight aluminum or composite materials are used to solve the large scale test model development issues in subsonic, transonic and supersonic conditions; secondly, combination of dynamics and kinematics simulation analysis means are adopted, to realize and optimize high load test device for transmission mechanism design, and to solve the difficult design problem of α、β coupling double rotating shaft supporting structure; at last, the development ideas of the test and control system part are presented, the accuracy of the test system is improved furthermore through some technical means, including the motor selection, electromagnetic interference shielding, filter design techniques and so on. The technical indicators of the test system are also presented, M number ranges from 0.4 to 4.25, angle of attack from -35° to 35° and sideslip angle -15° to 15°, the bearing load of the transmission mechanism is up to no more than 10000 N. The test results of the SDM standard model show that the direct damping derivative is in good agreement with the reference data, and the repeatability error of the test data is within 10%. The application of this system for an aircraft model is presented, reasonable and reliable test data are obtained successfully.