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变幅多轴疲劳寿命分析方法对比

刘天奇 时新红 张建宇 费斌军

刘天奇, 时新红, 张建宇, 等 . 变幅多轴疲劳寿命分析方法对比[J]. 北京航空航天大学学报, 2018, 44(10): 2176-2184. doi: 10.13700/j.bh.1001-5965.2017.0782
引用本文: 刘天奇, 时新红, 张建宇, 等 . 变幅多轴疲劳寿命分析方法对比[J]. 北京航空航天大学学报, 2018, 44(10): 2176-2184. doi: 10.13700/j.bh.1001-5965.2017.0782
LIU Tianqi, SHI Xinhong, ZHANG Jianyu, et al. Comparative study of variable amplitude multiaxial fatigue life analysis methods[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(10): 2176-2184. doi: 10.13700/j.bh.1001-5965.2017.0782(in Chinese)
Citation: LIU Tianqi, SHI Xinhong, ZHANG Jianyu, et al. Comparative study of variable amplitude multiaxial fatigue life analysis methods[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(10): 2176-2184. doi: 10.13700/j.bh.1001-5965.2017.0782(in Chinese)

变幅多轴疲劳寿命分析方法对比

doi: 10.13700/j.bh.1001-5965.2017.0782
基金项目: 

国家自然科学基金 11172021

详细信息
    作者简介:

    刘天奇  男, 博士研究生。主要研究方向:结构疲劳可靠性

    时新红  女, 讲师。主要研究方向:结构疲劳可靠性

    通讯作者:

    时新红, E-mail:shixinhong@buaa.edu.cn

  • 中图分类号: V215.5+2

Comparative study of variable amplitude multiaxial fatigue life analysis methods

Funds: 

National Natural Science Foundation of China 11172021

More Information
  • 摘要:

    基于当前对变幅多轴疲劳的研究,首先简要回顾了3种常用的变幅多轴疲劳寿命分析方法,包括Bannantine-Socie方法、Wang-Brown方法及王雷-王德俊方法。之后介绍了3种方法在程序中实现的具体方式,并对3种方法进行了编程实现。最后采用以上3种方法对飞机某结构危险部位在飞机服役过程中所承受的应力(应变)谱进行了分析,得到了3种方法的预测寿命。此外,为了比较多轴疲劳载荷对该结构寿命的影响,采用单轴的Manson-Coffin方程对该结构进行了寿命分析。通过对各方法的寿命分析结果对比分析,Wang-Brown方法的预测结果比较合理,王雷-王德俊方法的预测结果偏保守,Bannantine-Socie方法的预测结果较其他2类方法偏大,而单轴疲劳寿命分析方法会给出较为危险的预测结果。

     

  • 图 1  Bannantine-Socie方法流程图

    Figure 1.  Flowchart of Bannantine-Socie method

    图 2  空间任意平面上单位向量

    Figure 2.  Unit vector on an arbitrary plane of space

    图 3  Wang-Brown方法流程图

    Figure 3.  Flowchart of Wang-Brown method

    图 4  王雷-王德俊方法流程图

    Figure 4.  Flowchart of Wang L-Wang D J method

    图 5  结构的应力云图及危险部位

    Figure 5.  Stress contour and critical site of structure

    图 6  飞机某结构危险部位承受的应变-时间历程

    Figure 6.  Strain-time history of an aircraft structure's dangerous part

    图 7  飞机某结构危险部位承受的应力-时间历程

    Figure 7.  Stress-time history of an aircraft structure's dangerous part

    表  1  7B04铝合金材料的力学性能

    Table  1.   Mechanical properties of 7B04 aluminum alloy

    力学性能数值
    E/GPa70
    σ0.2/MPa449
    σu/MPa490
    ν0.3
    σ′f/MPa916
    b-0.080 3
    ε′f0.231 6
    c-0.873 4
    下载: 导出CSV

    表  2  飞机某结构危险部位载荷谱排列顺序

    Table  2.   Load spectrum arrangement sequence of an aircraft structure's dangerous part

    飞行起落数起落类型
    1A
    2B
    3A
    4B
    5A
    6B
    7A
    8D
    9C
    10D
    11B
    12A
    13B
    14A
    15B
    16A
    17B
    18C
    19D
    20C
    下载: 导出CSV

    表  3  各方法疲劳寿命预测结果

    Table  3.   Results of fatigue life estimated by different methods

    预测结果Bannantine-Socie方法Wang-Brown方法王雷-王德俊方法Manson-Coffin方程
    S=0.5S=1.0S=1.5S=2.0
    预测寿命(谱块)125.2225.7107.366.547.844.2581.9
    飞行起落数2 5044 5142 1461 33095688411 638
    下载: 导出CSV
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  • 收稿日期:  2017-12-19
  • 录用日期:  2018-02-25
  • 刊出日期:  2018-10-20

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