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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
[ "陈 磊(1983-),男,陕西西安人,硕士,工程师,2006年于长春理工大学获得学士学位,2014年于西南科技大学获得硕士学位,现为中国空气动力研究与发展中心超高速空气动力研究所工程师,主要从事流动显示与光学测量方面的研究。E-mail:158229332@qq.com" ]
[ "徐 洋(1989-),男,吉林吉林人,博士,工程师,2019年于空军工程大学获得博士学位,现为中国空气动力研究与发展中心超高速空气动力研究所工程师,主要从事方向:空空对外对抗仿真,风洞非接触测量技术研究与应用。E-mail:mingze0108@126.com" ]
收稿日期:2021-06-02,
修回日期:2021-08-13,
纸质出版日期:2022-02-25
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陈磊,徐洋,许晓斌等.窗口玻璃畸变校正下的自由飞模型姿态测量技术研究[J].光学精密工程,2022,30(04):455-463.
CHEN Lei,XU Yang,XU Xiaobin,et al.Research on attitude measurement technology of free flying model under window distortion correction[J].Optics and Precision Engineering,2022,30(04):455-463.
陈磊,徐洋,许晓斌等.窗口玻璃畸变校正下的自由飞模型姿态测量技术研究[J].光学精密工程,2022,30(04):455-463. DOI: 10.37188/OPE.20223004.0455.
CHEN Lei,XU Yang,XU Xiaobin,et al.Research on attitude measurement technology of free flying model under window distortion correction[J].Optics and Precision Engineering,2022,30(04):455-463. DOI: 10.37188/OPE.20223004.0455.
高超声速风洞试验中,模型的姿态信息是试验数据是否可靠的重要判断依据,其测量精度对试验结果有着重要影响。双目视觉测量系统能测量高超声速风洞自由飞试验模型的姿态参数,通常将其放在风洞试验段外,通过试验段壁上窗口玻璃观测试验段内部的模型。然而,窗口玻璃产生的成像畸变将降低系统的测量精度。为此,本文提出了窗口玻璃成像畸变校正下的自由飞模型姿态测量技术。通过对窗口玻璃折射造成像面畸变进行建模,提出基于标记点线性拟合的校正方法,快速减小成像畸变。在此基础上,在
Φ
1 m高超声速风洞试验现场搭建了视觉测量系统。试验结果表明:当测量范围为1 m×1 m×1 m时,测量精度优于0.5 mm,并完成了自由飞试验模型六自由度姿态的测量工作,满足气动数据分析的要求。
During hypersonic wind tunnel tests, the pose information of a model supports the reliability of the experimental data, and the measurement accuracy of these data has a significant impact on the test results. Binocular vision measurement systems can measure the attitude parameters of free flight test models in a hypersonic wind tunnel. The system is usually placed outside of the wind tunnel test section and observes the model through a glass window situated on a wall of the test section. However, the glass window distorts the image and reduces the measurement accuracy. This paper proposes a measurement method to correct the glass window distortion. By modeling the image surface distortion caused by refraction through the glass window, a correction method is proposed based on the linear fitting of marker points to eliminate the image distortion and improve the measurement accuracy. Moreover, a binocular vision measurement system is developed at the scene of the
Φ
1 m hypersonic wind tunnel test, and a six degrees of freedom attitude of a free flight model is successfully measured. The results show that the measuring accuracy was greater than 0.5 mm when the measuring range was 1 m × 1 m × 1 m. Therefore, the system satisfies the requirements of subsequent pneumatic data analysis.
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