期刊文献+

一种改进的多处损伤平板的剩余强度模型 被引量:1

Improved Link up Model for Residual Strength of Flat Aluminum Panels with Multiple Site Damages
在线阅读 下载PDF
导出
摘要 进行了多处损伤平板的剩余强度试验研究,得到不同裂纹几何平板的剩余强度。试验结果表明主裂纹长度增加使平板的剩余强度减小;对相同的主裂纹长度,韧带减小,试验件剩余强度也减小。以试验数据为基础,提出了一种修正的塑性区连通准则。用塑性区连通准则和修正的塑性区连通准则分别计算了多处损伤平板的剩余强度,结果表明对不同的主裂纹长度和不同的韧带长度,塑性区连通准则预测的平均误差为16.07%,而修正的Swift塑性区连通准则的平均误差为9.24%,大大提高了预测结果的精度。 The residual strength of fiat aluminum panels with multiple site damage was investigated experimen-tally, and the residual strengths of these panels in different crack sizes were obtained. The experimental results showed that the residual strengths of the panels would decrease as the lead crack length increased and in case when the ligament reduced for the same lead crack size. Based on these experimental results, an improved plastic zone link up model was presented. The residual strengths of flat aluminum panels with multiple site damages were evalu-ated with the plastic zone link up model and the improved plastic zone link up model respectively. It is shown that for the panels with different lead crack sizes and different ligament length, the average errors were 16.07% and 9.24% respectively for these two models, showing the notable improvement in prediction with the improved model.
出处 《科学技术与工程》 2008年第2期451-456,共6页 Science Technology and Engineering
关键词 多处损伤 剩余强度 主裂纹 韧带 塑性区连通 multiple site damage residual strength lead crack ligament plastic zone linkup
  • 相关文献

参考文献9

  • 1[1]Gruber M.Investigation of fuselage structure subject to widespread fa-tigue damage,DOT/FAA/AR-95/47,Office of Aviation Research-Washington D C,1996
  • 2[2]Dela Motte E B,Opalski F A.MSD:where we are and where we should go.Paper Presented at and U.S.Air force Structural Integrity Conference,San Antonio,Texas,December 1993
  • 3[3]Swift T.Widespread fatigue damage monitoring issues and concerns,the 5th International Conference on Structural Airworthiness of New and Aging Aircraft,Hamburg,Germany,Janel6-18,1993
  • 4[4]Chen Chuin-Shan,Paul A,Ingraffea A R.Residual strength pre-dictionin KC-135 fuselage and curvilinear crack growth analysis in narrow body fuselages.Proceedings of the 5th Joint NASA/FAA/DOD Conference on Aging Aircraft,2001
  • 5[5]Cherry M C,Mall S,Heinemann M B,et al.Residual strength of unstiffened aluminum panels with multiple site damage,Engineering Fracture Mechanics,1997;57(6):70l-713
  • 6李仲,刘亚龙,王生楠,葛森,吕国志.广布疲劳损伤加筋板结构剩余强度分析[J].机械强度,2006,28(5):747-750. 被引量:8
  • 7[7]Dhar J P Gallagher,Berens,A P,Bums JG.A comparison of frac-ture criteria forcrack coalescence and other observations based on re.sidual strength calculations.Paper Presented at and U.S.Air force Structural Integrity Conference,San Antonio,Texas,December 1993
  • 8[8]Kamei A,Yokobori T.Two collinear asymmetrical elastic cracks.Report of the Research Institute for Strenth and Fracture of Materi-als,tohoku University,1974;10:4l-42
  • 9[9]Grandt A F Jr.Stressintensity factors for some thru-eracked fastener holes.International Journal of Fracture,1975;5(2):283-294

二级参考文献2

共引文献7

同被引文献3

引证文献1

二级引证文献2

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部