固体力学与飞行器总体设计

缺口件振动疲劳寿命分析的名义应力法

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  • 1. 南京航空航天大学 飞行器先进设计技术国防重点学科实验室, 江苏 南京 210016;
    2. 成都飞机设计研究所, 四川 成都 610041
李德勇(1985- ) 男,助理工程师。主要研究方向:结构振动疲劳分析。 E-mail: leaderyong@126.com 姚卫星(1957- ) 男,博士,教授,博士生导师。主要研究方向:飞行器结构设计。 Tel: 025-84892177 E-mail: wxyao@nuaa.edu.cn

收稿日期: 2011-01-24

  修回日期: 2011-02-21

  网络出版日期: 2011-11-24

基金资助

611所航空基金(C1007-011)

Nominal Stress Approach for Life Prediction of Notched Specimens Under Vibration Loading

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  • 1. Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicles, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
    2. Chengdu Aircraft Design & Research Institute, Chengdu 610041, China

Received date: 2011-01-24

  Revised date: 2011-02-21

  Online published: 2011-11-24

摘要

为了描述缺口根部应力均方根(RMS)的集中程度,给出了缺口件在动态载荷激励下的应力均方集中系数的定义及其计算公式。基于结构疲劳的基本机理,通过考察缺口根部应力均方根的分布特点,给出了疲劳缺口系数的计算公式,形成了缺口件振动疲劳寿命分析的名义应力法。通过3个算例的计算结果表明,本文提出的方法能很好地预测缺口件的振动疲劳寿命。

本文引用格式

李德勇, 姚卫星 . 缺口件振动疲劳寿命分析的名义应力法[J]. 航空学报, 2011 , 32(11) : 2036 -2041 . DOI: CNKI:11-1929/V.20110419.1703.007

Abstract

To describe the centralized level of the stress root mean square (RMS) around a notch, this paper proposes a definition and calculation formula of the stress mean square concentration factor for notched specimens under dynamic excitation. A calculation formula for notch fatigue factor is presented based on the basic fatigue mechanism of structures and a consideration of the distribution characteristics of the stress root mean square in dangerous regions around a notch. Consequently the nominal stress approach for the life prediction of notched specimens under vibration loading is obtained. The results of three typical examples show that the method proposed in this paper can predict the vibration fatigue life of notched specimens well.

参考文献

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