摘要
为了满足大型飞机机身段壁板对接面区域的高质量制孔要求,提出基于六轴联动环形轨自动化制孔系统的孔位修正方法.该方法采用激光位移传感器以非接触测量的方式测量并求解得到基准孔的法矢,结合视觉测量系统获取的基准孔孔位误差,通过插值Coons曲面方法计算待加工孔的孔位误差向量,并补偿至理论坐标,实现孔位修正.利用筒状飞机机身壁板模型对该方法进行验证.结果表明,与双线性插补方法相比,该方法综合考虑了壁板外形表面曲率变化因素,孔位修正精度较高,保证了机身段壁板对接区域制孔的几何精度要求.
A method of hole position correction for a flexible track automatic drilling system with six axes was proposed in order to meet the high drilling accuracy requirement of aerospace fuselage join assembly.The method was presented by measuring and computing the normal vector of the reference holes through four non-contact laser displacement sensors.The error of reference holes can be obtained based on the vision measurement system.A position correction method using error data of reference holes was developed by interpolating the Coons surface.Then the position correction can be realized by adding error to the nominal coordinates of the holes.The method was tested on a cylinder model.Results indicate that the method accounting for the changing curvature of the panel shape has higher accuracy of hole position correction and can effectively meet the geometric accuracy requirement of aircraft panels compared with the double linear interpolating method.
出处
《浙江大学学报（工学版）》
EI
CAS
CSCD
北大核心
2015年第10期1863-1869,共7页
Journal of Zhejiang University：Engineering Science
基金
国家自然科学基金资助项目(51275463)
关键词
环形轨自动化制孔系统
激光位移传感器
法矢
COONS曲面
孔位修正
flexible track automatic drilling system
laser displacement sensor
normal vector
Coons surface
hole position correction
