CAJ | 학술논문

飞机部件之间存在着复杂的连接关系，连接件用于传递载荷和固定部件，一旦发生问题，影响重大。本研究针对在役飞机垂尾与机身对接结构处频发裂纹和紧固件松动故障，按照故障树初步分析影响因素，通过有限元及频响函数进一步计算诊断，并针对结构设计、刚度匹配、强制装配对流场中结构振动问题的影响进行了讨论。分析表明：蒙皮局部突起造成气流紊乱加之发动机振动为连接部位裂纹和紧固件松动的直接原因。针对分析结果，通过改进零件结构、加工方式以提高构件疲劳性能，局部补强以减小后机身局部振动方面完善设计，目前已经过飞行验证，分析过程及改善措施合理有效。
비궤부건지간존재착복잡적련접관계，련접건용우전체재하화고정부건，일단발생문제，영향중대。본연구침대재역비궤수미여궤신대접결구처빈발렬문화긴고건송동고장，안조고장수초보분석영향인소，통과유한원급빈향함수진일보계산진단，병침대결구설계、강도필배、강제장배대류장중결구진동문제적영향진행료토론。분석표명：몽피국부돌기조성기류문란가지발동궤진동위련접부위렬문화긴고건송동적직접원인。침대분석결과，통과개진령건결구、가공방식이제고구건피로성능，국부보강이감소후궤신국부진동방면완선설계，목전이경과비행험증，분석과정급개선조시합리유효。
Airplane was assembled by thousands of components. The joining components were the most important parts to transfer load and fix other compents. The failure of these components would badly influence the security of airplane. This paper discussed failure of structure joining the vertical empennage and fuselage on the airplane. The failure form was crack and fastener non-fixing. Fault-tree was used to analyse the crack failure primarily;correlative structures were simulated with CAE( computer aided engineer) software that analyzed stress and vibration of structure and then the effect of vibration of structure was discussed from structure desigining, stiffness matching, and forced assembly. The results show that the cracks of joining structure were mainly caused by airflow orifice on the fuselage;the airflow orifice disorganized air along the course of airplane. In addition,the vibration of engine promoted the initiation and propagation of the cracks. According to the analysis results, re-designing structure shape and improving processing manner were implanted to improve the anti-fatigue strength, local stiffened structure was used to reduce vibration . Corresponding correcting steps were validated by flight presently.