力学与实践 ›› 2011, Vol. 33 ›› Issue (3): 46-49.DOI: 10.6052/1000-0879-lxysj2010-510

• 应用研究 • 上一篇    下一篇

含广布腐蚀坑结构寿命评估方法

董妍,任克亮,刘平平,高士武   

  1. 宁夏大学物理电气信息学院
  • 收稿日期:2010-12-23 修回日期:2011-02-23 出版日期:2011-06-15 发布日期:2011-06-21
  • 通讯作者: 任克亮
  • 基金资助:
    国家自然基金;教育部重点研究项目;宁夏回族自治区自然科学基金

MULTIPLESITE CORROSION DAMAGE ASSESSMENT

  • Received:2010-12-23 Revised:2011-02-23 Online:2011-06-15 Published:2011-06-21
  • Contact: Ren ke-liang
  • Supported by:
    National Natural Science Foundation of Chian; Key Project of Chinese Ministry of Education;Ningxia Natural Science Foundation of China

摘要: 为了定量评估含广布腐蚀损伤老龄化飞机结构的剩余强度, 采用等效裂纹方法将腐蚀坑沿垂 直于外界最大主应力方向进行投影处理, 使其转化为具有相同寿命的等效初始表面裂纹, 然 后采用参数化有限元方法,求解等效裂纹前沿的应力强度因子、裂纹扩展方向和裂纹扩展增量, 建立并应用应力强度因子变化历程, 采用循环接循环的损伤累积方法对含广布等效表面裂纹 在疲劳载荷作用下的寿命进行了预测. 预测结果为复杂环境中含广布腐蚀坑的飞机结构寿命 预测提供了参考.

关键词: 疲劳寿命

Abstract: In order to quantitatively assess the residual strength of the aging aircraft with widespread corrosion damages the equivalent crack size technique is used to simulate the surface corrosion pits as initial surface cracks on corrosion structure, where a hypothetical initial surface crack with the same life as the corrosion pit is used. Thus the analysis of the corrosion structure with numerous pits becomes a problem of multiple surface cracks. Then, the parameter finite element method and the cycle-by-cycle iterative algorithm are used to compute the stress intensity factor, crack extension directions, and crack-growth increments. When the stress intensity factor history is obtained using the crack-growth increment and stress intensity factors, the fatigue life of the structure under fatigue loading is estimated through cycle-by-cycle damage accumulation. The result provides a guidance for fatigue life prediction of an aircraft structure with widespread corrosion pits in complicated environments.

Key words: fatigue life

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