北京航空航天大学学报 ›› 2000, Vol. 26 ›› Issue (6): 691-693.

• 论文 • 上一篇    下一篇

改进的耐久性分析裂纹萌生方法研究

刘文1, 刘彤2   

  1. 1. 北京航空航天大学 飞行器设计与应用力学系;
    2. 清华大学 材料科学与工程
  • 收稿日期:1999-07-20 发布日期:2010-11-19
  • 作者简介:刘文(1940-),男,河北高阳人,教授,100083,北京.

Research on Improved Crack Initiation Approach of Durability Analysis

LIU Wen-ting1, LIU Tong2   

  1. 1. Beijing University of Aeronautics and Astronautics, Dept. of Flight Vehicle Desigh and Applied Mechanics;
    2. Tsinghua University, Dept. of Materials Science and Engineering
  • Received:1999-07-20 Published:2010-11-19

摘要: 针对耐久性分析裂纹萌生方法所存在的影响其工程应用效果的3个重要问题,加以研究和改进.在结构使用载荷谱下进行一组模拟试件的耐久性试验;依据裂纹萌生寿命试验数据,用计算反推法确定结构细节裂纹萌生p-s-N曲线三参数式的参数cp;分析了对数裂纹萌生寿命标准差对经济寿命的重要影响,取该标准差值为飞机结构对数疲劳寿命的常用标准差值0.176~0.2,从而建立了能够准确预测结构经济寿命的改进的耐久性裂纹萌生方法.这种方法已在我国多种飞机结构的耐久性评定中得到成功的应用.

Abstract: There are three important shortages having influence on engineering application in crack initiation approach of durability analysis established.They are researched and improved in this paper.Durability test for a group of analogous specimens is carried out under service load spectrum of the structure.On the basis of test data of crack initial life,the factors cp in three-parameter formula of crack initial p-s-N curves for structural details are determined by backward compute method. After analyzing big influence of standard deviation of logarithm crack initial life on economic life,this standard deviation is made as 0.176~0.2 that is general value for logarithm fatigue life of aircraft structures. Then an improved crack initiation approach of durability analysis is developed and is successfully applied for the durability evaluation of aircraft structures.

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