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中文摘要：
对飞机结构螺接件来说,最主要的强度问题之一,是在疲劳载荷下会产生裂纹并扩展。而目前对含裂纹螺接件的应力强度因子（Stress intensity factor,SIF）分析多以简化的二维有限元模型为主。为此,在考虑螺栓与孔壁间的非线性接触、摩擦和螺栓预紧力等因素影响的基础上,利用非线性有限元软件MSC.Marc构建含裂纹螺接件的三维有限元分析模型,通过分析得到不同损伤模式下的SIF与裂纹长度沿板厚度方向的变化曲线。结果表明,虽然螺接件孔边裂纹是复合型裂纹,但Ⅰ型SIF起主导作用,Ⅱ型和Ⅲ型SIF可忽略不计;在裂纹长度一定时,接触面处的SIF最大,外表面处最小,孔边双侧裂纹对称时的SIF大于孔边单侧裂纹情形;裂纹长度相同时,含沉孔螺接件接触面上的SIF大于直孔情形时相应的SIF,而外表面的SIF趋势则恰恰相反。
英文摘要：
One of the major strength problems for bolted joint of aircraft is the onset and growth of cracks due to fatigue loading.But at present,the analysis of stress intensity factor（SIF） for bolted joint with crack are mainly based on two-dimensional finite element model.For that,three-dimensional（3D）finite element model of a bolted joint with cracks has been developed using the non-linear finite element code MSC Marc.Issues in modeling non-linear touching,and the friction between the joint parts,and the pre-stress force of bolt are all taken into account.SIF solutions along the thickness of bolted joint are obtained for different damage models.The results show that KⅠ is dominant,and KⅡ and KⅢ have small contributions although the crack model beside hole is complex.SIF reaches maximum at the faying surface and minimum at the outside surface for all crack length.For a given crack length,SIF of a symmetric crack is always higher than the one of an asymmetric crack.SIF at the faying surfacing for countersunk is higher than that for straight hole for same crack length.But the trend of SIF at the outside surface is opposite.In other words,the type of fastener hole has a great influence on SIF of bolted joint.
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