Design and implementationfor full field of view measurement scheme in vertical wind tunnel
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摘要: 尾旋运动是飞机的一种非正常的极限飞行状态，复杂并且危险，极易造成飞行事故。在立式风洞中开展尾旋实验是研究尾旋现象的主要技术手段之一，目的是为了获取实验过程中模型飞机的姿态角，用于对其尾旋特性进行分析。针对尾旋实验运动状态的特点，以及双目测量系统在以往实验应用中的缺陷，设计了一种全视场测量方案，并围绕其关键技术问题开展了研究，使用编码标记识别技术实现特征标记的自动识别，通过基于刚体的三维重建技术实现模型姿态的测量，采用基于共同基准平面的数据标定方法实现多视角姿态数据的有效融合。通过立式风洞尾旋实验验证了该技术的有效性及可靠性，实验结果曲线完整，图像利用率达到了95%，为尾旋运动特性分析提供了更加丰富的数据支撑。Abstract: Spin is a kind of abnormal state of aircraft, complicated and dangerous. It can easily cause flight accident. Spin experiment in vertical wind tunnel is one of the main research technical means. The purpose is to obtain the attitude angle of model aircraft in experimental process, for analysis of its spin characteristics. The paper concentrates its attention on the characteristics of spin motion and the application defect of binocular measurement system in previous experiments. The full field of view measurement scheme is designed, and the research for the key technologies is carried out. The coded marker recognition technology is adopted to realize feature automatic identification. The 3D reconstruction technology based on rigid body is adopted to realize the measurement of model attitude. The date calibration based on the same reference plane is adopted to realize the effective data fusion within multiple angles of view. The effectiveness and reliability of the measurement technology is proved by spin experiment in vertical wind tunnel. The experiment curves are complete, and the image utilization reaches 95%. It provides richer data for characteristics analysis of spin phenomenon.
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Key words:
- spin /
- vertical wind tunnel /
- coded marker /
- full field of view
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表 1 实验数据统计
Table 1. Statistics of test data
尾旋
状态总图像
数量双目测量
系统识别
数量双目测量
系统图像
利用率全视场
系统识别
数量全视场
测量系统
图像利用率正飞平
尾旋1123 72 59% 120 97% 正飞平
尾旋2113 63 56% 107 95% 倒飞平
尾旋1116 66 57% 100 95% 倒飞平
尾旋2141 75 53% 137 97% 倒飞振
荡尾旋156 83 53% 149 96% 
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