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针对带工字梁结构的飞机某复合材料构件在共固化成型后不可避免产生位置随机偏差以及定位基准位置偏差引起安装定位误差,并由此给工字梁上的铆接孔和单曲面蒙皮法向孔采用数控程序制孔带来困难甚至无法进行的问题,提出了通过在位测量构件特征点位置偏差并据此修正已有数控制孔程序实现其自动制孔的工艺方法,给出了特征点位置偏差测量原理、误差数学模型和数控程序修正策略,为实现某复合材料构件的数字化加工奠定了良好的技术基础。
For the I-beam structure of a composite member of the aircraft after the co-curing molding position will inevitably produce random deviation and positioning the reference position deviation caused by the installation of positioning errors, and thus to the I-beam riveting holes and single-surface skin The problem that the normal hole is difficult or even impossible to make by the numerical control program is put forward. The method of measuring the characteristic position of the component by in-position measurement and correcting the existing number of control hole program is proposed, Point position deviation measurement principle, error mathematical model and numerical control program correction strategy for the realization of a composite material digital processing has laid a good technical foundation.