主要介绍了一套用于３ｍ低速风洞的俯仰－滚转两自由度大振幅非定常实验系统。该系统由三大部分组成：俯仰－滚转两自由度的模型动态支撑机构；俯仰－滚转两自由度电控液压系统；数据采集与处理软件系统。该系统可以在风洞中真实模拟飞行器姿态变化，并测量其相应的六分量非定常气动力变化。为飞行器的飞行力学动态性能分析或飞行模拟器提供非定常气动力数据。另外，用三角翼在３ｍ风洞进行了多种运动状态的非定常气动力特性测量，结果真实地反映了大迎角与大滚转角时三角翼的非定常气动特性 A set of large-amplitude unsteady experiment system of pitch-roll two-degree-of-freedom for 3m low speed wind tunnel is introduced. The system consists of three parts: the pitch - rolling two degrees of freedom model dynamic support mechanism; pitch - roll two degrees of freedom electric control hydraulic system; data acquisition and processing software system. The system can simulate the change of attitude of the aircraft in the wind tunnel and measure the corresponding six-component unsteady aerodynamic changes. It provides unsteady aerodynamic data for aircraft aerodynamic performance analysis or flight simulator. In addition, the unsteady aerodynamic characteristics of a variety of movement states were measured by the delta wing at 3m wind tunnel. The results truly reflected the unsteady aerodynamic characteristics of the delta wing at high attack angles and large roll angles