|
| 铝合金整体壁板时效成形-轴压承载联合仿真方法与试验验证 |
| Co-simulation of Aging Forming and Axial Compression Load-bearing for Aluminum Alloy Integral Panel and Experimental Verification |
| Received:November 14, 2024 |
| DOI：10.3969/j.issn.1674-6457.2025.02.003 |
| 中文关键词: 7B50铝合金 整体壁板 时效成形 屈曲分析 有限元 |
| 英文关键词: 7B50 aluminum alloy integral panel aging forming buckling analysis finite element (FE) |
| 基金项目:珠海市创新创业团队项目(2120004000459);国家自然科学基金联合基金重点支持项目(U22A20190);国家自然科学基金(52475418，52205435) |
| Author Name | Affiliation | | TONG Canyu | AVIC General Huanan Aircraft Industry Co., Ltd., Guangdong Zhuhai 519042, China | | WANG Yongmei | AVIC General Huanan Aircraft Industry Co., Ltd., Guangdong Zhuhai 519042, China | | DU Juan | AVIC General Huanan Aircraft Industry Co., Ltd., Guangdong Zhuhai 519042, China | | ZHAN Lihua | Light Alloy Research Institute of Central South University, Central South University, Changsha 410083, China | | YANG Youliang | Light Alloy Research Institute of Central South University, Central South University, Changsha 410083, China | | XU Yongqian | Light Alloy Research Institute of Central South University, Central South University, Changsha 410083, China | | WANG Chen | AVIC General Huanan Aircraft Industry Co., Ltd., Guangdong Zhuhai 519042, China | | XU Lingzhi | AVIC General Huanan Aircraft Industry Co., Ltd., Guangdong Zhuhai 519042, China |
|
| Hits: 16 |
| Download times: 2 |
| 中文摘要: |
| 目的 以航空7xxx系铝合金整体壁板为研究对象，建立时效成形仿真和轴压承载仿真的联合仿真方法，研究时效成形工艺对壁板承载能力的影响，提高成形壁板的承载载荷预测精度。方法 基于ABAQUS的整体壁板CREEP子程序成形仿真结果，开发UMAT子程序，将屈服强度的大小及分布等成形结果信息引入轴压承载仿真模型中，从而实现考虑成形工艺影响的整体壁板非线性屈曲仿真模拟和极限载荷预测，并开展了时效成形壁板的轴压承载试验。为了对比，还进行了基于人工时效材料强度的机加壁板轴压承载仿真。结果 通过联合仿真计算得到的成形壁板极限承载载荷为1 055 kN，与成形壁板极限载荷试验值的相对误差为1.1%，而机加壁板仿真计算结果为1 182 kN，与成形壁板试验值的相对误差为13.2%。分析壁板在轴压仿真过程中的应力情况可知，与机加壁板相比，时效成形壁板的材料强度有所降低，因此，它先达到结构承载极限并发生失稳，仿真模型的破坏形式与试验件的一致。结论 铝合金整体壁板时效成形-轴压承载联合仿真能准确预测时效成形壁板的结构承载能力，为整体壁板的设计-制造-强度校核一体化提供了新的计算方法。 |
| 英文摘要: |
| The work aims to develop a co-simulation method of aging forming and axial compression load-bearing for 7xxx series aluminum alloy aviation integral panel to study the influence of aging forming process on the bearing capacity of the panel and improve the accuracy of bearing load prediction with 7xxx series aluminum alloy integral panels for aviation as the research objects. Based on the forming simulation result of CREEP subroutines of integral panels in ABAQUS, an UMAT subroutine was developed to introduce the forming results, such as the yield strength size and distribution, into the bearing simulation model, so as to realize the nonlinear buckling simulation and bearing capacity prediction of the integral panel considering the influence of forming process. And the corresponding axial compression tests of the age-formed panel were carried out. For comparison, axial compression bearing simulations were also conducted on the machined panel based on the yield strength of artificial aging alloy. The ultimate bearing load of the formed panel calculated by co-simulation was 1 055 kN, and relative error with the experimental value of the formed panel was 1.1%; while the simulation result of the machined panel was 1 182 kN and the relative error with the experimental value of the formed panel was 13.2%. By analyzing the stress of the panel during the process of axial compression simulation, it was found that the age-formed panel had a lower yield strength, which led to the reduced bearing limit and increased susceptibility to instability compared with the machined panel. Moreover, the failure mode of age-formed panel simulation was in good agreement with the experimental result. The proposed co-simulation of aging forming and bearing test can accurately predict the load-bearing capacity of age-formed panels, and provides a new method for the integration of design, manufacture and strength check of aviation integral panels. |
|
View Full Text
View/Add Comment Download reader |
| Close |
|
|
|
渝公网安备 50010702501719号