中文摘要：

在飞机装配中制孔的位置精度直接影响飞机的最终装配质量,自动化制孔以飞机数模为基准,受装配误差影响,在机翼翼盒等封闭结构中,难以确保制孔位置与骨架沟槽关键特征的边距满足工艺要求。提出一种基于孔边距约束和Shepard插值的自动化制孔位置评价及修正方法,通过激光跟踪仪及扫描仪获取实测骨架点云数据并进行去噪和配准,将骨架理论孔位映射到点云模型获得实际制孔位置,提取骨架沟槽关键特征的边界点并构造Ferguson曲线作为边界曲线,基于此计算制孔约束区域中实际孔位的边距及孔边距偏差。针对孔边距可能超差的情况,提出一种先基于孔边距偏差修正约束孔位再利用Shepard插值法修正其余孔位的孔位修正策略,在满足孔边距要求的同时保留了原孔位的行列分布特性。运用所提出的方法对某型飞机机翼骨架进行测量和数据处理,验证了该方法的有效性。

英文摘要：

The position accuracy of holes directly affects the quality of aircraft final assembly.Automatic drilling relies on aircraft CAD model,which is influenced by the assembly errors.In closed structure such as aircraft wing,it is hard to ensure the distance between the hole center and the boundary of trench of skeleton.Then,a correction method for hole positions based on hole margin constraints and Shepard interpolation is proposed.Firstly,laser tracker and T-Scan are used to collect point cloud data of wing skeleton and then the data is processed through de-noising and registration.Then,actual hole positions are calculated by projecting reference holes on skeleton model to point cloud.And local boundary feature points are extracted,which are used to fit a Ferguson curve as the local boundary of key feature.Finally,the deviations of actual and theoretical constraint hole margin are calculated.For the deviation exceeding the preset tolerance,the positions of constraint holes are firstly corrected based on hole margin deviation and the other holes are corrected by Shepard interpolation.To demonstrate the validity of this method,an aircraft wing is measured and the data is processed to correct hole positions,which shows that the hole positions can be corrected and the distribution characteristics of original holes can be reserved.