测量高超声速风洞试验中模型颤振数据对飞行器安全设计至关重要，接触式传感器测量存在精度低、使用不便等缺点。本文采用非接触式立体视觉三维测量技术，测量试验过程中模型表面关键点的振动变形，为模型颤振分析提供基础数据。为了克服试验过程中试验段内的气压从真空到常压交替变化引起的强烈振动，通过设计视觉测量系统密封装置与气浮减振器，将视觉三维测量装备放置到Φ1 m高超声速风洞试验段内，并提出基于模型关键点与系统参数同时求解的系统参数自校准算法，消除试验段环境振动引起的测量误差。试验结果表明：在测量范围为1 m×1 m×1 m、相机分辨率为1 000×1 000 pixel时，系统的测量精度优于0.1 mm，满足高超声速风洞试验模型颤振的测量需求。

The measurement of model flutter data in hypersonic wind tunnel tests is crucial for the safety design of aircraft. However， contact sensors yield a low measurement accuracy and are inconvenient to use. Therefore， this study adopts the non-contact 3D vision measurement technology to measure the vibration of key points on the surface of a model during the test process for the model flutter analysis. The existing measurement systems can only be placed outside the window glass of the test section. Owing to the limitation of the size of the window glass and the influence of the image distortion caused by the glass， the measurement accuracy cannot meet the requirements for the flutter measurement of a hypersonic wind tunnel test model. Placing the measuring system in the test section is an effective approach to solve the above-mentioned problems. However， in the test process， the air pressure in the test section alternates sharply between vacuum and normal pressure， with strong vibration； thus， the existing visual 3D measurement systems cannot be placed in the test section. In this study， through the design of the sealing device and the air floating shock absorber of the visual measurement system， the visual 3D measurement equipment， for the first time， is placed on the platform in the test section of a 1 m hypersonic wind tunnel， and a self-calibration algorithm based on the simultaneous solution of the key points of the model and the system parameters is proposed to eliminate the measurement error caused by the environmental vibration in the test section. The results indicate that in the measurement range of 1 m×1 m×1 m， the camera resolution is 1 000×1 000 pixels，and the measurement accuracy of the system can be greater than 0.1 mm，thereby meeting the requirements for the flutter measurement of a hypersonic wind tunnel test model.