飞机蒙皮零件数控精确拉形技术应用研究
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摘要
以某大型客机蒙皮零件为例,设计了基于数字化工艺设计与有限元仿真的数控精确拉伸成形技术方案。基于毛料面内变形状态分析设计了多工步拉形加载轨迹,通过"虚拟拉形"有限元模拟比较了多种纵拉和横拉方案及相应工艺参数下的成形质量。有限元模拟结果表明,该零件采用横拉方案效果优于纵拉方案,并根据有限元模拟结果优化了空间加载轨迹参数。根据设备求解生成数控代码,在Cyril Bath L2x350数控拉伸机上直接进行了自动化拉伸成形试验,获得了合格的零件,并比较验证了有限元分析和测量数据结果,验证了设计的飞机蒙皮零件数控精确拉形技术方案的可行性和准确性。
Taking a large-scale passenger aircraft skin part as example,a precision computer numerical control( CNC) stretch forming technical framework was established based on digital process design and finite element simulation. The loading trajectory of multi-step stretch forming was designed based on the analysis of the in-plane deformation state of sheet metal. The forming quality under various longitudinal and transversal stretch forming schemes and corresponding process parameters was compared by using ‘virtual stretch forming'finite element simulation. The finite element simulation results show that the transversal scheme is better than longitudinal schemes. Then the 3 D loading trajectory parameters were optimized by finite element simulation result. The automatic stretch forming experiments were carried out directly on the Cyril Bath L2 x350 stretching machine by using the CNC code reverse calculated based on the CNC equipment,and qualified parts were obtained. The finite element simulation results and experiment data were compared to verify the feasibility and accuracy of the technical framework of precision CNC stretch forming of aircraft skin components.
Taking a large-scale passenger aircraft skin part as example,a precision computer numerical control( CNC) stretch forming technical framework was established based on digital process design and finite element simulation. The loading trajectory of multi-step stretch forming was designed based on the analysis of the in-plane deformation state of sheet metal. The forming quality under various longitudinal and transversal stretch forming schemes and corresponding process parameters was compared by using ‘virtual stretch forming'finite element simulation. The finite element simulation results show that the transversal scheme is better than longitudinal schemes. Then the 3 D loading trajectory parameters were optimized by finite element simulation result. The automatic stretch forming experiments were carried out directly on the Cyril Bath L2 x350 stretching machine by using the CNC code reverse calculated based on the CNC equipment,and qualified parts were obtained. The finite element simulation results and experiment data were compared to verify the feasibility and accuracy of the technical framework of precision CNC stretch forming of aircraft skin components.
引文
[1]曾元松.航空钣金成形技术[M].北京:航空工业出版社,2014.ZENG Yuansong. The sheet metal forming technology in aviation industry[M]. Beijing:Aviation Industry Press,2014.
[2]李卫东,万敏,金海霞.飞机蒙皮拉形计算机辅助工程系统ASSFCAE[J].塑性工程学报,2005,12(增刊):200-203.LI Weidong,WAN Min,JIN Haixia. Computer aided engineering system for aircraft stretch forming[J]. Journal of Plasticity Engineering,2005,12(S):200-203.
[3] ODING S S. Controlling the formation of double curvature skin elements on a program-controlled stretch former[J]. Izvestiya VUZ.Aviatsionnaya Tekhnika,1987,30(3):47-51.
[4] PENG J W,LI W D,HAN J Q,et al. Kinetic locus design for longitudinal stretch forming of aircraft skin components[J]. International Journal of Advanced Manufacturing Technology,2016,86(9):3571-3582.
[5]韩金全,万敏,陈雪梅,等.飞机复杂蒙皮拉形工艺参数优化设计[J].塑性工程学报,2009,16(6):96-101.HAN Jinquan,WAN Min,CHEN Xuemei,et al. Optimization of process parameters in stretch forming of aircraft complex skin[J].Journal of Plasticity Engineering,2009,16(6):96-101.
[6]刘垒,徐应强.飞机前缘蒙皮数字化精确拉形技术[J].南京航空航天大学学报,2012,44(S1):79-82.LIU Lei,XU Yingqiang. Numerical precise stretch forming for airplane leading-edge skin component[J]. Journal of Nanjing University of Aeronautics&Astronautics,2012,44(S1):79-82.
[7]谭富星,许旭东,李光俊,等.柔性夹持多点拉形过程的数值模拟[J].西安交通大学学报,2008,42(9):1160-1164.TAN Fuxing,XU Xudong,LI Guangjun,et al. Numerical simulation for process of multi-point stretch forming with flexible clamp mode[J]. Journal of Xi'an Jiaotong University,2008,42(9):1160-1164.
[2]李卫东,万敏,金海霞.飞机蒙皮拉形计算机辅助工程系统ASSFCAE[J].塑性工程学报,2005,12(增刊):200-203.LI Weidong,WAN Min,JIN Haixia. Computer aided engineering system for aircraft stretch forming[J]. Journal of Plasticity Engineering,2005,12(S):200-203.
[3] ODING S S. Controlling the formation of double curvature skin elements on a program-controlled stretch former[J]. Izvestiya VUZ.Aviatsionnaya Tekhnika,1987,30(3):47-51.
[4] PENG J W,LI W D,HAN J Q,et al. Kinetic locus design for longitudinal stretch forming of aircraft skin components[J]. International Journal of Advanced Manufacturing Technology,2016,86(9):3571-3582.
[5]韩金全,万敏,陈雪梅,等.飞机复杂蒙皮拉形工艺参数优化设计[J].塑性工程学报,2009,16(6):96-101.HAN Jinquan,WAN Min,CHEN Xuemei,et al. Optimization of process parameters in stretch forming of aircraft complex skin[J].Journal of Plasticity Engineering,2009,16(6):96-101.
[6]刘垒,徐应强.飞机前缘蒙皮数字化精确拉形技术[J].南京航空航天大学学报,2012,44(S1):79-82.LIU Lei,XU Yingqiang. Numerical precise stretch forming for airplane leading-edge skin component[J]. Journal of Nanjing University of Aeronautics&Astronautics,2012,44(S1):79-82.
[7]谭富星,许旭东,李光俊,等.柔性夹持多点拉形过程的数值模拟[J].西安交通大学学报,2008,42(9):1160-1164.TAN Fuxing,XU Xudong,LI Guangjun,et al. Numerical simulation for process of multi-point stretch forming with flexible clamp mode[J]. Journal of Xi'an Jiaotong University,2008,42(9):1160-1164.