高超声速风洞下的双目视觉测量技术研究  

Binocular Vision Measurement Technology in Hypersonic Wind Tunnel

作　　者：徐洋 陈磊[1] 许晓斌[1] 王雄[1] 马晓宇[1] 何超[1] XU Yang;CHEN Lei;XU Xiaobin;WANG Xiong;MA Xiaoyu;HE Chao(Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心超高速空气动力研究所,四川绵阳621000

出　　处：《电光与控制》2022年第2期72-75,92,共5页Electronics Optics & Control

基　　金：大科学装置前沿研究(2020YFA0405700)。

摘　　要：针对高超声速风洞试验段内来流过强、总压总温过高导致的光学测量设备不易布局的问题,设计了一种适用于高超声速风洞的双目视觉测量系统布局方案及姿态测量方法。通过试验段内外布置的高速相机及LED光源,实现对测试模型六自由度数据的采集;为了验证布局合理性,利用静态试验加以验证,采用双目视觉系统中模型标志点技术解算模型位移和姿态信息。通过在试验中与实际送进机构对模型姿态的改变量进行对比,证明了双目视觉系统布置方案的可行性,同时验证了此系统在测量距离1.2 m、测量空间范围0.5 m^(3)内,对模型转动姿态测试误差低于0.08°,位移测试误差低于0.05 mm。Due to excessive oncoming flow,high total pressure and high total temperature in the test section of a hypersonic wind tunnel,it is difficult to design the layout of optical measurement equipment.To solve this problem,a layout scheme of the binocular vision measurement system as well as the attitude measurement method is designed,which is suitable for hypersonic wind tunnels.Through the high-speed cameras and LED light sources arranged inside and outside the test section,the 6-DOF data of the test model is collected.In order to verify the rationality of the layout,static tests are conducted,and the mark-point technology in the binocular vision system is adopted to calculate the displacement and attitude of the model.In the experiment,a comparison with the actual feeding mechanism on the change of the model’s attitude is conducted,which verifies the feasibility of the layout scheme of the binocular vision system.Within a distance of 1.2 m and a space of 0.5 m^(3),the test error of rotation attitude is lower than 0.08°,and the test error of displacement is lower than 0.05 mm.

关 键 词：高超声速风洞 双目视觉 标志点 姿态测量 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]