航空学报 > 1987, Vol. 8 Issue (2): 115-118

疲劳门槛值及低速裂纹扩展速率试验方法的研究进展

丁传富, 赵伟, 顾明达   

  1. 北京航空材料研究所
  • 收稿日期:1985-11-21 修回日期:1900-01-01 出版日期:1987-02-25 发布日期:1987-02-25

IMPROVEMENTS IN TEST METHOD FOR FATIGUE THRESHOLDS AND LOW FATIGUE CRACK GROWTH RATE

Ding Chuanfu, Zhao Wei, Gu Mingda   

  1. Beijing Institute of Aeronautical Materials
  • Received:1985-11-21 Revised:1900-01-01 Online:1987-02-25 Published:1987-02-25

摘要: 一、引言 近年来,国内外研究者对疲劳门槛值⊿K_(th)及附近的低速裂纹扩展速率已进行了许多实验研究,提出了多种不同的试验方法。但到日前为止,还无统一的标准试验方法,给疲劳门槛值的实验研究提供交流,以及在工程上的应用造成了很大困难。为此,有必要研究和制定统一的标准试验方法。本文根据近年来我们对疲劳门槛值所做的实验研究工作,着重讨论了我们对ASTM推荐测定疲劳门槛值及低速裂纹扩展速率暂行试

Abstract: The test method for fatigue thresholds and low fatigue crack growth rate are discussed and some improvements are made to the tentative ASTM test method for K and low fatigue crack growth rate. They are mainly as follows.1.The load-shedding parameters and the corresponding crack growth increaments for recommended procedures are: load-shedding ratio R = 510%; K-decreassing gradient C=-0.2- 0.05mm; crack growth interval a = 0. 250.5mm.2.The relationship among specimen width, specimen type, load-shedding procedures and the maximum final crack length is presented.3. In data reduction, lg (da/dN) is recommended as the independent variable in the linear regression scheme to determine K or da/dN in stage region.4.A BASIC computer program for performing the test of fatigue thresholds and low fatigue crack growth rate in accordance with the proposed method is given.The improved method is more complete, reliable and applicable. It has been adopted in the national standard test method for fatigue crack growth rate.