CAJ | 학술논문

连接件是飞机结构中常见的承载结构，但也是常见的疲劳源，连接件上紧固件钉传载荷和孔边旁路载荷直接影响疲劳寿命，采用bush元、beam元和rbar模拟紧固件和板的连接关系，建立了连接件细节有限元模型。为降低端部孔的应力集中，使连接板的厚度呈台阶形状，计算紧固件载荷的分布，然后通过应力严重系数法，确定各个连接件结构的严重孔，最后对各个严重孔的疲劳寿命进行了对比，计算结果表明与理论相符，对结构的优化设计具有参考价值。
련접건시비궤결구중상견적승재결구，단야시상견적피로원，련접건상긴고건정전재하화공변방로재하직접영향피로수명，채용bush원、beam원화rbar모의긴고건화판적련접관계，건립료련접건세절유한원모형。위강저단부공적응력집중，사련접판적후도정태계형상，계산긴고건재하적분포，연후통과응력엄중계수법，학정각개련접건결구적엄중공，최후대각개엄중공적피로수명진행료대비，계산결과표명여이론상부，대결구적우화설계구유삼고개치。
The joint is the common bearing structure in the aircraft ,but it’s also a common source of fatigue .The pin load on the fasteners and the bypass load on the side of hole directly affect the fatigue life .The fasteners and plate con‐nection relationship simulated by the bush element ,beam element and rbar element in the article .Established the joint detail finite element model .thickness of connecting plate shape steps ,Which can reduce the stress concentration of the end hole .And calculate the load distribution .Then determine the serious hole in the various joints ,by Stress Severity Factor approach .Finally the fatigue life of various serious holes were compared ,the calculation results show that accords with the theory ,the optimization of structure design has reference value .