| 基于原位拉伸测定GTN损伤模型参数的5052铝合金成形极限应力图研究(英文) |
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| 引用本文： | 何敏,李付国,王志刚.基于原位拉伸测定GTN损伤模型参数的5052铝合金成形极限应力图研究(英文)[J].中国航空学报,2011(3):378-386. |
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| 作者姓名： | 何敏 李付国 王志刚 |
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| 作者单位： | 西北工业大学材料科学与工程学院;徐州工程学院机电工程学院;中航工业第一飞机设计研究院结构设计研究所; |
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| 基金项目： | Aeronautical Science Foundation of China(03H53048) |
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| 摘 要： | 传统成形极限图(FLD)由第一主应变与第二主应变的比值构成。但FLD依赖于成形历史和应变路径。因此,本文采用成形极限应力图(FLSD)来预测铝合金5052-O1(AA5052-O1)的成形极限。将修订的Gurson-Tvergaard-Needleman(GTN)塑性势模型用来模拟Nakazima凸模胀形实验。采用带扫描电镜(SEM)的原位拉伸试验观察记录损伤演化过程以确定GTN模型中的材料参数。通过计算AA5052-O1三个损伤阶段的孔洞分数获得GTN模型参数。根据实验结果,原生孔洞体积分数、最大形核孔洞体积分数、临界孔洞体积分数,最终断裂孔洞体积分数分别为0.002918,0.0249,0.030103,0.04854。在断裂前最后一个载荷步获得的应力应变值用来绘制AA5052-O1的FLSD和FLD。与Nakazima凸模胀形试验和单轴拉伸试验结果相比较,预测结果与试验结果较为吻合。由原位拉伸试验确定的模型参数可用于研究韧性金属的成形极限。
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| 关 键 词： | 成形极限应力图 GTN模型 原位拉伸实验 孔洞损伤 AA5052-O1板 |
Forming Limit Stress Diagram Prediction of Aluminum Alloy 5052 Based on GTN Model Parameters Determined by In Situ Tensile Test |
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| HE Mina,b,LI Fuguoa,WANG Zhigang.Forming Limit Stress Diagram Prediction of Aluminum Alloy 5052 Based on GTN Model Parameters Determined by In Situ Tensile Test[J].Chinese Journal of Aeronautics,2011(3):378-386. |
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| Authors: | HE Mina b LI Fuguoa WANG Zhigang |
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| Institution: | c aSchool of Materials Science and Engineering,Northwestern Polytechnical University,Xi’an 710072,China bDepartment of Mechanical Science and Engineering,Xuzhou Institute of Technology,Xuzhou 221008,China cDepartment of Aircraft Structure Design and Research,the First Aircraft Institute,Aviation Industry Corporation of China,Xi’an 710089,China |
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| Abstract: | The conventional forming limit diagram (FLD) is described as a plot of major strain versus minor strain.However,FLD is dependent on forming history and strain path.In the present study,a forming limit stress-based diagram (FLSD) has been adopted to predict the fracture limit of aluminum alloy (AA) 5052-O1 sheet.Nakazima test is simulated by plastic constitutive formula derived from the modified Gurson-Tvergaard-Needleman (GTN) model.An in situ tensile test with scanning electron microscope (SEM) is proposed... |
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| Keywords: | forming limit stress diagram GTN model in situ tensile test void damage aluminum alloy 5052-O1 sheet metal forming |
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