摘要
对机翼13肋过渡梁及副油箱挂架进行了总体有限元分析,得到了后接头吊挂区为疲劳危险区域。在细节应力分析时,建立了轴承连接,得到了吊挂轴承开孔区的细节应力分布。以此静力结果为基础,编制随机疲劳载荷谱,使用FE-safe疲劳分析程序得到轴承开孔区的裂纹形成寿命,该寿命不满足飞机6000次起落的寿命目标。通过对后接头的耳片加宽至52mm,或者加厚至12mm时,可满足飞机的寿命目标。
Complete finite element analysis（FEA） is conducted on pylon of auxiliary fuel tank（PAFT） under the thirteenth wing ribs, and we select suspension region as the critical dangerous point though the result. The bearing connection is considered in local FEA to get the stress distribution. According to the stress results, random load spectrums are made, and the fatigue life computation of bearing connection region is completed using FE-safe. The results show that the fatigue life does not meet the requirement of 6000 cycles unless the width or thickness of the back joint＇s lug is changed to 52 mm or 12 mm.
出处
《航空制造技术》
2016年第7期66-68,72,共4页
Aeronautical Manufacturing Technology
关键词
疲劳危险点
疲劳寿命
细节应力
副油箱挂架
Fatigue dangerous point
Fatigue life
Local stress
Pylon of auxiliary fuel tank
