可修复结构破坏危险性分析

RELIABILITY AND RISK ANALYSIS OF REPAIRABLE AIRFRAME COMPONENTS

在全面考虑影响结构破坏危险性多种主要随机因素的基础上，重点研究了将定期检查时查出的破损结构修复并重新投入使用情况下的结构破坏危险性分析方法。建立了相应的分析模型，并以某型国产歼击机机翼主梁为例，给出了分析计算结果。结果表明：对于长寿命飞机结构，在使用后期，忽略修复并重新投入使用的结构将是偏危险的。

A reliability and risk analysis methodology is developed for airframe components under scheduled inspection and repair maintenance in service. It is assumed that critical locations in the airframe components are fastener holes,of which the initial fatigue quality(IFQ)is repre- sented by the equivalent initial flaw size(EIFS).a fastener hole must be repaired when a crack is detected. after repair,the fatigue quality of the airframe components is assumed to be renewed,in the sense that the flaw size distribution of the repaired fastener holes is identical to that of the new fastener hole. In this analysis,many quantities involving statistical variabilities have been taken into account,for instance,the initial fatigue quality,crack propagation,residual strength,ervice loading,crack detection probability,etc. A numerical example for the wing main spar of some fighter is given. The numerical results show that the developed analysis methodology is applicable.