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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°。
High-speed aircraft fuel tank separation pose parameters is an important basic data aircraft and fuel tank design. Most of the attitude and attitude measurement work is carried out in the wind tunnel environment which simulates the flying state of the aircraft. The non-contact measurement of the contraction ratio model is implemented. Due to the observation window limitation in the wind tunnel test section and the influence of the shape of the auxiliary tank model, it is very difficult to measure the pose of the auxiliary tank model. Firstly, aiming at the effect of wind tunnel observation window and the complicated environment of wind tunnel on the image acquisition effect, the image acquisition method based on self-luminous unit is put forward. The binocular vision system is used to acquire the clear sequence image of the object. Secondly, Based on the wraparound color coding method, the matching method of self-luminous mark points can be used to match the mark points in the complex environment of wind tunnel. Finally, the pose information of the tank model is obtained according to the three-dimensional coordinates of the cooperation mark points on the surface of the sub tank. The experimental results show that the proposed attitude measurement method meets the measurement requirements, the maximum displacement error does not exceed 0.102mm and the maximum angle error does not exceed 0.201 °.