摘要
飞机机翼前缘蒙皮,由于其形状和成形材料的特点使拉形结束卸载回弹后会产生较大的回弹量,对零件的成形质量影响较大。文章分析机翼前缘蒙皮零件的典型成形方案,确定主要加载轨迹参数,利用正交试验设计方法设计拉形工艺方案,通过有限元模拟和结果分析,获得了主要工艺参数对成形零件回弹量的影响规律。针对某前缘蒙皮零件,根据有限元分析结果,对工艺参数进行设计和优化,通过生产性试验,获得了成形质量较好的试验零件,并进行厚度、应变测量和对比分析,验证了有限元模拟的精度。
The wing leading edge skin may have large springback after unloading due to the characteristics of shape and material.The typical forming method of wing leading edge skin stretch forming was analyzed to determine loading path parameters.The orthogonal experiment method was used to design stretch forming processes,and finite element simulation was also used to reveal the influence of the process parameters on the springback.Aimed at a typical wing leading edge skin part,process parameters was designed and optimized according to the results of finite element simulation.Productive experiments were carried out by the designed parameters.The accuracy of finite element simulation was verified by thickness and strain measurement and comparison with finite element simulation results.
出处
《塑性工程学报》
CAS
CSCD
北大核心
2011年第4期74-78,共5页
Journal of Plasticity Engineering
基金
国家"863计划"资助项目(2007AA04Z1A3)
中国商飞大型客机科研攻关资助项目(SAMF09-07-JS-074)
关键词
蒙皮拉形
前缘蒙皮
参数优化
试验
有限元法
skin stretch forming
parameters optimization
experimental research
wing leading edge skin
finite element method
