CAJ | 학술논문

飞行器结构的多裂纹是导致结构可靠性降低和破坏的主要原因，在考虑结构多裂纹之间相互影响的基础上对飞行器多裂纹结构进行剩余强度可靠性研究，并探寻影响剩余强度及其可靠性的主要原因。首先通过建立断裂力学有限元模型对飞行器典型MSD（ Multiple-Site Damage）壁板结构进行确定性的剩余强度计算；接着在剩余强度和载荷分别服从Weibull分布和正态分布的基础上，建立了MSD壁板的剩余强度可靠性模型；最后通过数值积分对一组2024-T3 MSD壁板进行了剩余强度及其失效概率计算。对比结果显示采用该方法得到的计算结果与试验得到的结构失效概率基本一致。该方法考虑了裂纹间的相互影响、裂纹扩展阻力曲线、剩余强度和载荷的概率分布等方面的因素，可为研究飞行器结构多裂纹现象提供一定的支持。
비행기결구적다렬문시도치결구가고성강저화파배적주요원인，재고필결구다렬문지간상호영향적기출상대비행기다렬문결구진행잉여강도가고성연구，병탐심영향잉여강도급기가고성적주요원인。수선통과건립단렬역학유한원모형대비행기전형MSD（ Multiple-Site Damage）벽판결구진행학정성적잉여강도계산；접착재잉여강도화재하분별복종Weibull분포화정태분포적기출상，건립료MSD벽판적잉여강도가고성모형；최후통과수치적분대일조2024-T3 MSD벽판진행료잉여강도급기실효개솔계산。대비결과현시채용해방법득도적계산결과여시험득도적결구실효개솔기본일치。해방법고필료렬문간적상호영향、렬문확전조력곡선、잉여강도화재하적개솔분포등방면적인소，가위연구비행기결구다렬문현상제공일정적지지。
Multiple-crack on the aircraft structure is a major cause the influences adversely structure reliability and integrity. An approach which considers interaction of cracks and stable tearing is employed to calculate the residual strength of Multiple-Site Damage( MSD) panel. Fracture mechanism finite element model of a certain MSD panel is used to evaluate the residual strength;both fracture toughness and R-curve are considered. On the basis of Weibull distribution of residual strength and normal distribution of load, the residual strength reliability model is developed. Numerical results of 2024-T3 aluminum alloy MSD panels are compared with the test results. The agreement between analysis and experiment is shown to be reasonable. Comparison indicates preliminarily that the proposed approach can give a better prediction and will be useful for investigating MSD panel on aircraft structure.