2024铝合金航空座椅支承零件等温模锻成形研究  

Study on isothermal mould forging for aviation seat supporting parts of aluminum alloy 2024

作　　者：郭奕文[1] 邓运来[1,2,3] 王宇[2] 刘胜胆[2,3] 

机构地区：[1]中南大学轻合金研究院,湖南长沙410083 [2]中南大学材料科学与工程学院,湖南长沙410083 [3]中南大学有色金属材料科学与工程教育部重点试验室,湖南长沙410083

出　　处：《锻压技术》2016年第8期12-17,共6页Forging & Stamping Technology

基　　金：国家重点基础研究发展计划(2012CB619505)

摘　　要：采用Deform-3D有限元软件及等温模锻试验对2024铝合金航空座椅支承零件的成形过程进行了模拟与试验研究,并且分别对等温模锻件和热轧板机加工零件的组织和性能进行了对比研究。结果表明,在420℃、锻压速度为1.5 mm·s-1、保压时间为1.5~2 min的锻造工艺参数条件下,2024铝合金航空座椅支承零件锻造成形的最大锻压力为12700 k N,锻件成形金属流动顺利。在本文的工艺条件下试制锻造了多件2024铝合金航空座椅支承件,测试分析结果表明,通过等温模锻制造的航空座椅支承零件较热轧板机加工零件强度提高11.4%,最高的强度为508 MPa,且不同方向力学性能的差异小于3%。The forming process of aviation seat supporting parts for aluminum alloy 2024 was simulated and tested by Deform-3D finite element software and isothermal mould forging test respectively. Furthermore,the microstructure and mechanical properties of isothermal mould forging and machined parts of hot rolled plate were studied comparatively. The results show that under the condition of temperature of 420 ℃,forging speed of 1. 5 mm·s- 1and pressure holding time of 1. 5- 2 min,the highest forging force is up to 12700 k N,and the metal flows smoothly on the forging mould. Several pieces of forged aluminum alloy 2024 aviation seats supporting parts are produced under the above-mentioned condition. Test and analysis results show that its strength increases about 12% and achieves 508 MPa compared with the machined parts,and the differences among the mechanical properties of different directions are less than 3%.

关 键 词：Deform-3D模拟 等温模锻 2024铝合金 热轧板 航空座椅支承零件 

分 类 号：V261.32[航空宇航科学与技术—航空宇航制造工程] TG319[金属学及工艺—金属压力加工]