综合考虑载荷谱和结构特性分散的概率断裂力学方法

doi:10.7527/S1000-6893.2014.0198

固体力学与飞行器总体设计

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综合考虑载荷谱和结构特性分散的概率断裂力学方法

贺小帆¹, 董颖豪¹, 李玉海², 刘文珽¹

1. 北京航空航天大学航空科学与工程学院, 北京 100191;
2. 中国航空工业集团公司, 北京 100022

收稿日期:2014-04-14 修回日期:2014-08-25 出版日期:2015-04-15 发布日期:2014-09-12
通讯作者: 贺小帆Tel.: 010-82315738 E-mail: xfhe@buaa.edu.cn E-mail:xfhe@buaa.edu.cn
作者简介:贺小帆男, 博士, 副教授。主要研究方向: 疲劳/断裂,结构可靠性与耐久性,腐蚀条件下使用寿命评定。Tel: 010-82315738 E-mail: xfhe@buaa.edu.cn;董颖豪男, 博士研究生。主要研究方向: 结构可靠性与耐久性。Tel: 010-82315738 E-mail: buaadyh@126.com;李玉海男, 博士, 研究员。主要研究方向: 飞机结构疲劳寿命与可靠性。Tel: 024-86368001 E-mail: lyh601@263.net刘文珽男, 学士, 教授。主要研究方向: 疲劳与断裂力学,概率断裂力学,结构耐久性与损伤容限技术,结构可靠性,腐蚀条件下的结构寿命。Tel: 010-82315738 E-mail: lwt_jiang@163.com
基金资助:
省部级项目

Probabilistic fracture mechanics approach accounting for both the variability of load spectra and of structural properties

HE Xiaofan¹, DONG Yinghao¹, LI Yuhai², LIU Wenting¹

1. School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China;
2. Aviation Industry Corporation of China, Beijing 100022, China

Received:2014-04-14 Revised:2014-08-25 Online:2015-04-15 Published:2014-09-12
Supported by:
Ministry Level Project

摘要/Abstract

摘要：

在飞机结构的设计定型阶段,要综合考虑载荷谱和结构特性的分散评估机群的可靠寿命。为此,进行了某型飞机结构细节的TA15M钛合金模拟试件在3个单机谱下的耐久性试验,断口判读得到主裂纹扩展(a,t)数据,反推得到了当量初始缺陷尺寸(EIFS)。对比分析表明,载荷谱分散对EIFS分布参数无影响,估计得到了通用EIFS分布参数。建立了考虑载荷谱分散的裂纹扩展对数正态随机变量模型及参数估计方法,由此确定裂纹超越概率并进行损伤度评估,建立了综合考虑载荷谱和结构特性分散的概率断裂力学方法(PFMA)。

关键词: 飞机结构, 耐久性, 载荷谱分散, EIFS, 载荷谱损伤, 概率断裂力学

Abstract:

In the design phase of aircraft structures, the fleet reliability should be evaluated accounting for both the variability of load spectra and of structural properties. For reliability life evaluation, a durability test under three individual load spectra is conducted for the specimens of TA15M titanium alloys stimulating the aircraft structure details. The lead crack growth (a,t) data are obtained. As a result, the equivalent initial flaw size (EIFS) values are back-extrapolated. Statistical analysis demonstrates that the variability of load spectra has no obvious influence on the EIFS distribution. The general EIFS distribution parameters are subsequently estimated. A log-normal random variable model is derived analytically to describe the crack growth rule accounting for the variability of load spectra and pertinent parameter estimation method is given, upon which the probability of crack exceedance is derived and the extent of damage is evaluated. Consequently, a probabilistic fracture mechanics approach (PFMA) is developed accounting for both the variability of load spectra and of structural properties.

Key words: aircraft structures, durability, variability of load spectra, EIFS, load spectrum damage, probabilistic fracture mechanics

中图分类号:

V215.5

贺小帆, 董颖豪, 李玉海, 刘文珽. 综合考虑载荷谱和结构特性分散的概率断裂力学方法[J]. 航空学报, 2015, 36(4): 1142-1149.

HE Xiaofan, DONG Yinghao, LI Yuhai, LIU Wenting. Probabilistic fracture mechanics approach accounting for both the variability of load spectra and of structural properties[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(4): 1142-1149.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

综合考虑载荷谱和结构特性分散的概率断裂力学方法

Probabilistic fracture mechanics approach accounting for both the variability of load spectra and of structural properties

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