摘要
在飞机结构件加工过程中,铝合金厚板内的残余应力会使其产生变形,导致飞机结构件无法满足加工精度要求。为此,通过研究淬火-拉伸有限元仿真关键技术,建立了淬火仿真与预拉伸仿真方法。结果表明,淬火应力在分布趋势和幅值大小方面,仿真值均与实验值都非常吻合,最大相对误差只有10%左右。然后将板材离散为若干层,依据淬火残余应力及拉伸所产生的尺寸变化率,推导出各层屈服极限及弹性模量的变化,分析材料非均匀性对残余应力的影响规律。对50mm厚的淬火铝合金板材进行预拉伸仿真分析时发现,残余应力的仿真结果与实验测量数据呈现相同的分布特征。最后,通过对不同厚度的铝厚板进行淬火-拉伸仿真,揭示不同铝厚板内残余应力的变化规律。
During the processing of aircraft structural components,the residual stress within the thick aluminum alloy plates will cause them to deform,resulting in the aircraft structural components failing to meet the requirements of machining accuracy.In order to address this issue,by studying the key technologies of finite element simulation for quenching and stretching,the methods for quenching simulation and pre-stretching simulation were established.The results show that the simulated values of the quenching stress are in very good agreement with the experimental values,both in terms of the distribution trend and the magnitude.The maximum relative error is only about 10%.Then,the plate is discretized into several layers.Based on the quenching residual stress and the dimensional change rate generated by stretching,the changes in the yield limit and elastic modulus of each layer are deduced,and the influence law of material inhomogeneity on the residual stress was analyzed.When conducting pre-stretching simulation analysis on 50 mm-thick quenched aluminum alloy plate,the simulated values of the residual stress also exhibit the same distribution pattern as the experimental results.Finally,through the quenching-stretching simulation of thick aluminum plates with different thicknesses,the variation laws of the residual stress within different thick aluminum plates were revealed.
作者
秦国华
姜耀
林锋
王华敏
郭瑞超
QIN Guohua;JIANG Yao;LIN Feng;WANG Huamin;GUO Ruichao(School of Aeronautical Manufacturing Engineering,Nanchang Hangkong University,Nanchang 330063,China;College of Aeronautical Engineering,Shandong University of Aeronautics,Binzhou 256600,China)
出处
《中国有色金属学报》
北大核心
2025年第6期1967-1978,共12页
The Chinese Journal of Nonferrous Metals
基金
广西科技重大专项(桂科AA23023027-3)
江西省自然科学基金资助项目(20232ACB204019)
山东省高等学校“青创团队计划”资助项目(2023KJ275)
江西省教育厅科学技术研究项目青年项目(GJJ2401007)。
关键词
7075铝合金
淬火-预拉伸
拉伸率
残余应力
消除效果
7075 aluminum alloy
quenching-pre-stretching
stretching ratio
residual stress
elimination effect Received date:2024-12-03
Accepted date:2025-04-08 Corresponding author:LIN Feng
Tel:+86-15279120700
E-mail:70694@nchu.edu.cn
