板间摩擦对航空连接件疲劳性能的影响  

Friction Effects Between Plates on Fatigue Performance of Aircraft Joints

作　　者：舒文军[1] 何宇廷[1] 刘仁宇[1] 杜金强[1] 伍黎明[1] 

机构地区：[1]空军工程大学工程学院,西安710038

出　　处：《南京航空航天大学学报》2010年第3期347-350,共4页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国家高技术研究发展计划("八六三"计划)(2009AA04Z406)资助项目;国防"十一五"预研基金(513270501)资助项目

摘　　要：针对某型飞机外翼下壁板典型连接件结构,建立了三维有限元接触模型,对其细节弹塑性应力进行了分析,并利用局部应力应变法估算了其疲劳寿命。研究发现,连接件的疲劳性能对搭接板之间的摩擦条件是较为敏感的,随着摩擦系数的减少,板之间的摩擦力下降,孔边局部应力增大,连接件的疲劳性能下降。最后,对不同摩擦条件下的航空模拟搭接试件进行疲劳试验,试验结果与寿命估算结果较为一致,验证了分析方法的有效性。A three-dimensional contact model is established using ANSYS software based on the typical strap joint under the outer airplane wing. The detailed stress around bolt holes are analyzed. Then, the fatigue gap coefficient is obtained using the result of a three-dimensional model. And the fatigue life is obtained by Nuber formulas. It is found that the fatigue performance is susceptive of the friction be- tween plates. As the friction coefficient drops, The friction force between plates drops, so the increased load transferred by bolts results in an exacerbation of the local stress around holes. Inevitably, the fa- tigue performance of joints drops. Besides, when the friction coefficient drops, the dropping of fatigue performance accelerates. Meanwhile, based on the strap joint under the outer airplane wing, the fatigue life of specimens with different frictions is obtained through fatigue tests. It is verified that the estimated result of the three-dimensional model agrees with that of experimental data.

关 键 词：连接件 三维有限元模型 弹塑性分析 疲劳寿命 摩擦 

分 类 号：V2[航空宇航科学技术]