摘要
为了提高飞机数字化装配过程中翼身交点孔精加工的安全性,提出一种分析翼身接头相对装配参考坐标系的位姿误差的方法。采用矩阵摄动法建立了相应的误差模型,根据飞机大部件调姿试验的结果和相关工艺装备的性能参数,确定各项原始误差的取值范围。通过蒙特卡洛模拟求出翼身接头位姿误差的分布特性,在此基础上采用极值法定性分析极端情况下翼身交点孔的切削余量,获得了有可能出现翼身交点孔加工余量不足的定性结论。
To guarantee the security of finish machining of wing-fuselage connecting holes in aircraft digital assembly, a posture error analysis method of wing-fuselage joints is put forward relative to the reference frame of assembly system. The posture error model of wing-fuselage joints is built by using matrix perturbation method. The spans of each source error are determined according to results of fuselage posture alignment experiment and performance parameters of correlative equipments. Distribution of posture error of wing-fuselage joints is learned by Monte Carlo simulation. Cutting allowance of wing-fuselage connecting hole in the worst case is calculated by using extreme value analysis method. According to the calculation results, a qualitative conclusion was got and it＆#39;s a possibility that allowance of some wing-fuselage connecting holes is insufficient for finish machining.
出处
《航空精密制造技术》
2014年第1期38-42,共5页
Aviation Precision Manufacturing Technology
基金
国家自然科学基金资助项目(51305165)
浙江省教育厅科研计划项目(Y201226088)
关键词
数字化装配
位姿误差
仿真
机身-机翼接头
digital assembly
posture error
computer simulation
fuselage-wing joint
