摘要
开缝衬套冷挤压是国际航空制造中常用的孔强化技术,能够有效提高飞机连接寿命。A100超高强度钢与7050-T7451高强铝合金具有抗应力腐蚀性能强的优势,这两种材料的叠层组合形式被应用于飞机的主承力结构上。通过叠层冷挤压试验,分析挤压工序、挤压量、初孔直径等因素对叠层孔残余应力分布的影响。
Cold extrusion of slotted bushing is a commonly used hole strengthening technique in international aviation manufacturing,which can effectively improve the connecting life of aircraft.A100 ultra high strength steel and 7050-T7451 high strength aluminum alloy have the advantage of strong anti-stress corrosion performance.The laminated combination of these two materials is applied to the main bearing structure of aircraft.The influence of extrusion process,extrusion amount,initial hole diameter and other factors on the residual stress distribution of the lamination hole was analyzed through the lamination cold extrusion test.
出处
《科技视界》
2020年第31期104-106,共3页
Science & Technology Vision
关键词
孔强化
开缝衬套冷挤压
叠层结构
Hole strengthening
Cold extrusion of slotted bushing
The laminated structure
