常用宇航钣金材料成形极限图实验  

Experimental study on the forming limit diagrams(FLD)of aerospace sheet metal materials

作　　者：董文倩[1] 张小龙[1] 

机构地区：[1]上海航天精密机械研究所,上海201600

出　　处：《塑性工程学报》2014年第3期41-45,共5页Journal of Plasticity Engineering

摘　　要：对常用宇航钣金材料不锈钢1Cr18Ni9Ti、铝合金7A09、5A06、2A14、2A12及钛合金TC4进行成形极限的实验研究,得到1Cr18Ni9Ti、2A14、5A06及2A12室温下的FLD,并建立其FLD计算模型。实验结果表明,1Cr18Ni9Ti室温下的成形性能明显高于2A12、2A14和5A06,且金属板料厚度对其成形极限影响较大,板料越薄,成形极限越低。铝合金7A09及钛合金TC4在室温下的塑性成形性能极差,无法得到其室温下的FLD。The FLDs of the aerospace sheet metal materials of 1Cr18Ni9Ti stainless steel ,7A09、5A06、2A14、2A12 aluminum alloy and TC4 titanium alloy are studied by the experiments . The FLD calculating models of 1Cr18Ni9Ti ,5A06 ,2A14 and 2A12 are established based on the experimental data . The experimental study shows that the formability of 1Cr18Ni9Ti is much better than those of 5A06 ,2A14 and 2A12 under room temperature ,also the thickness of the sheet metal affects its forming limitation a lot . The thinner the sheet is , the lower of the forming limitation becomes . The formability of 7A09 aluminum alloy and TC4 titanium alloy are too bad to obtain their FLD under room temperature .

关 键 词：宇航钣金材料 成形极限图 计算模型 

分 类 号：TG386[金属学及工艺—金属压力加工]