新淬火状态2A12铝合金的成形极限
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摘要
对室温下分别时效10,20,30min的9种尺寸新淬火状态2A12铝合金试样在3种润滑(固体润滑,液体润滑和无润滑)条件下进行了胀形试验,得到了该铝合金的成形极限图,分析了时效时间对成形性能的影响。结果表明:时效10min时新淬火状态2A12铝合金仍具备良好的成形性能,但随时效时间的延长,成形极限曲线下移,铝合金的塑性变差,成形安全区变小;2A12铝合金成形加工前的自然时效时间应控制在10min以内。
As-quenched 2A12 aluminum alloy specimens with nine kinds of size obtained after aging at room temperature for 10,20,30 min,respectively,were bulged under three types of lubrication conditions including solid lubrication,liquid lubrication and no lubrication,respectively.The forming limit diagram of the aluminum alloy was obtained,and the effect of aging time on the formability was analyzed.The results show that the as-quenched 2A12 aluminum alloy obtained after aging for 10 min had good formability.With the increase of aging time,the forming limit curves moved down,indicating that the plasticity of the aluminum alloy decreased and the forming safety area became smaller.The appropriate natural aging time of 2A12 aluminum alloy before forming was within 10 min.
As-quenched 2A12 aluminum alloy specimens with nine kinds of size obtained after aging at room temperature for 10,20,30 min,respectively,were bulged under three types of lubrication conditions including solid lubrication,liquid lubrication and no lubrication,respectively.The forming limit diagram of the aluminum alloy was obtained,and the effect of aging time on the formability was analyzed.The results show that the as-quenched 2A12 aluminum alloy obtained after aging for 10 min had good formability.With the increase of aging time,the forming limit curves moved down,indicating that the plasticity of the aluminum alloy decreased and the forming safety area became smaller.The appropriate natural aging time of 2A12 aluminum alloy before forming was within 10 min.
引文
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[2]飞机设计手册总编委会.飞机设计手册:第3册上[M].北京:航空工业出版社,2004.
[3]KEELER S P,BACKOFEN W A.Plastic instability and fracture in sheets stretched over rigid punches[J].Trans ASM Q,1963,56(1):25-48.
[4]GOODWIN G M.Application of strain analysis to sheet metal forming problems in the press shop[C]//1968 Automotive Engineering Congress and Exposition.[S.l.]:SAE,1968:680093.
[5]王辉.成形极限图的获取方法与其在金属板料成形中的应用[D].南京:南京航空航天大学,2011.
[6]陈明和,高霖,薛玉雷,等.板料应力成形极限判据的有限元分析程序[J].南京航空航天大学学报,2005,37(增刊1):68-71.
[7]张成祥,陈明和,雷晓晶,等.GH600合金薄板成形极限研究[J].航空材料学报,2015,35(6):35-40.
[8]张成祥,陈明和,雷晓晶,等.GH163合金成形极限图及应用[J].塑性工程学报,2016,23(1):93-98.
[9]高宏志,周贤宾.新淬火状态铝合金板的成形极限[J].北京航空航天大学学报,2006,32(9):1083-1086.
[10]高宏志,周贤宾.新淬火状态硬铝合金板的成形性能及数值模拟[J].航空材料学报,2008,28(5):27-31.
[11]黄华,李大永,彭颖红.7075-T6铝合金板温热成形极限图实验[J].塑性工程学报,2010,17(1):93-97.
[12]陈劫实,周贤宾.板料成形极限预测新判据[J].机械工程学报,2009,45(4):64-69.
[13]DOEGE E,DRDER K.Sheet metal forming of magnesium wrought alloys:Formability and process technology[J].Journal of Materials Processing Technology,2001,115(1):14-19.
[14]LI D M,GHOSH A.Tensile deformation behavior of aluminum alloys at warm forming temperatures[J].Materials Science and Engineering:A,2003,352(1/2):279-286.
[15]陈新平,汪承璞.一种预测左半部成形极限图的简单方法[J].金属成形工程,2000,18(4):4-6.