Investigation on characteristic length testing methods for failure prediction of composite multi-bolt joints
Source abstract
Abstract
Characteristic lengths (CLs) are key factors in the characteristic curve method (CCM), which is widely used in engineering to predict the failure of composite multi-bolt joints. They directly affect the accuracy of predicting the joint failure. To identify suitable CL testing methods, six schemes have been designed and tested, in which two tensile CL specimens (open- and filled-hole laminates) and three compressive CL specimens (semi-circular notch laminates, pin-loaded hole laminates and single-bolt joints) have been compiled. Additionally, 3D FE analyses on the stress concentration have been performed and a discussion of the unit failure index curves of different specimens has been carried out to explore their load-carrying mechanism and determine why they result in different CLs. Failure predictions of composite multi-bolt joints by using the CCM with different CL testing schemes have been compared and evaluated using related static tensile experimental results. Filled-hole laminates for the tensile CL and single-bolt joints for the compressive CL are recommended because they best approximate the actual structure and obtain accurate failure predictions for composite multi-bolt joints.
Source: crossref · Quality: baseline
Research context
OpenAlex topics: Mechanical Behavior of Composites · Structural Load-Bearing Analysis · Fatigue and fracture mechanics
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
Affiliations
College of Aerospace Engineering, Chongqing University, Chongqing, PR China
School of Astronautics, Beihang University, Beijing, PR China
References (35)
Show source-provided references
1. Harris CE, Starnes JH and Shuart MJ. An assessment of the state-of-the-art in the design and manufacturing of large composite structures for aerospace vehicles . NASA/TM-2001-210844. Hampton: National Aeronautics and Space Administration, Langley Research Center, 2001.
2. 10.2514/2.299210.2514/2.2992 ↗
3. 10.1016/j.compscitech.2008.09.03710.1016/j.compscitech.2008.09.037 ↗
4. 10.1016/j.compscitech.2013.04.01810.1016/j.compscitech.2013.04.018 ↗
5. 10.1177/073168441350085910.1177/0731684413500859 ↗
6. 10.1177/073168441038503410.1177/0731684410385034 ↗
7. 10.1177/073168440808949310.1177/0731684408089493 ↗
8. 10.1177/073168440302200284810.1177/0731684403022002848 ↗
9. 10.1177/073168441039768110.1177/0731684410397681 ↗
10. 10.1177/073168441244465310.1177/0731684412444653 ↗
11. 10.1177/073168441038503410.1177/0731684410385034 ↗
12. 10.1177/00219983740080030310.1177/002199837400800303 ↗
13. 10.1016/S0263-8223(02)00056-910.1016/S0263-8223(02)00056-9 ↗
14. 10.1016/j.compscitech.2006.02.01710.1016/j.compscitech.2006.02.017 ↗
15. 10.1177/00219983820160060310.1177/002199838201600603 ↗
16. 10.1177/00219983840180030710.1177/002199838401800307 ↗
17. 10.1016/j.compstruct.2013.09.01910.1016/j.compstruct.2013.09.019 ↗
18. 10.1177/00219983960300120110.1177/002199839603001201 ↗
19. 10.1177/00219983960300140510.1177/002199839603001405 ↗
20. 10.1016/j.compstruct.2004.04.05310.1016/j.compstruct.2004.04.053 ↗
21. Yan UM, Sun HT, Wei WD, et al. Response and failure of composite plates with a bolt-filled hole . DOT/FAA/AR-97/85. Washington, DC: Office of Aviation Research, 1998.
22. 10.1016/S0263-8223(01)00005-810.1016/S0263-8223(01)00005-8 ↗
23. 10.1016/j.compstruct.2013.10.02610.1016/j.compstruct.2013.10.026 ↗
24. 10.1177/00219983900240050110.1177/002199839002400501 ↗
25. 10.1016/S1359-835X(99)00002-010.1016/S1359-835X(99)00002-0 ↗
26. 10.1177/002199831453902310.1177/0021998314539023 ↗
27. Hart-Smith LJ. Bolted joints in graphite-epoxy composites . NASA CR-144899. Long Beach: Douglas Aircraft Company, 1976.
28. 10.2514/3.5089210.2514/3.50892 ↗
29. Nelson WD, Bunin BL and Hart-Smith LJ. Critical joints in large composite aircraft structure . NASA-CR-3710. Long Beach: McDonnell Douglas Corporation, 1983.
30. Zhang JY, Liu FR, Zhao LB, et al. Influence of end distances on the failure of composite bolted joints. J Reinf Plast Compos 2015; DOI: 10.1177/0731684415572199.10.1177/0731684415572199 ↗
31. ASTM D 5766/ D 5766M-11 · 2011
32. ASTM D 5961/ D 5961M-13 · 2013
33. ASTM D 6742/ D 6742M-12 · 2012
34. Abaqus-Inc. ABAQUS Analysis User's Manual. Version 6.10. Dassault Systèmes; 2010.
35. 10.1016/j.compstruct.2013.01.00810.1016/j.compstruct.2013.01.008 ↗