摘要
高速飞行器副油箱分离位姿参数是飞行器以及副油箱设计的重要基础数据。位姿参数测量工作多在高度模拟飞行器飞行状态的风洞环境下进行,对缩比模型实施高速非接触测量。受风洞试验段观察视窗限制以及副油箱模型形状影响,副油箱模型位姿测量十分困难。首先针对风洞观察视窗以及风洞复杂环境对图像采集效果的影响,提出了基于自发光单元的副油箱运动序列图像采集方法,采用双目视觉系统高速采集获得目标物的清晰序列图像;其次,提出基于环绕式彩色编码的自发光标记点匹配方法,实现风洞复杂环境内标记点的高精度匹配;最后,根据副油箱表面合作标记点的三维坐标获取副油箱模型的位姿信息。试验结果表明:所提出的位姿测量方法满足测量要求,其最大位移误差不超过0.102mm、最大角度误差不超过0.201°。
Position and attitude parameters measured during the separation of fuel tanks from the high-speed flying aircraft are of great importantance in aircraft and auxiliary fuel tanks design. Pose parameter measuring needs to be carried out in wind tunnel environments with airflows in which highly simulated aircraft is flying, utilizing a high-speed non-contact measure- ment. The measurement of target position and attitude becomes even difficult due to the constraints from the observing win- dow and shape of the target, To reduce impacts from the observing window and the complex wind tunnel environment on the quality of captured images, an image acquisition method based on self-luminous units has been proposed, through which a clearer image sequence has been obtained. Moreover, a markers matching method based on the surrounding color-coding self-luminous units is presented to achieve high-precision matching of markers in complex wind tunnel environment. Finally, pose parameters of the auxiliary fuel tank can be calculated by analyzing the 3D coordinates of markers on the surface of the model. The experimental results indicate that the proposed method satisfies the measurement requirements, the maximum displacement error does not exceed 0. 102 mm and the maximum angle error is less than 0. 201°.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2015年第5期1556-1563,共8页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(51375075)
国家自然科学基金创新研究群体科学基金(51321004)~~
关键词
双目视觉
副油箱
彩色编码
位姿测量
风洞
binocular vision
auxiliary fuel tank
color-coding
position and attitude measurement
wind tunnel
