journal article·2008-03

Correction method for evaluation of interfacial fracture toughness of DCB, ENF and MMB specimens with residual thermal stresses

Tomohiro Yokozeki, Toshio Ogasawara, Takahira Aoki

Composites Science and Technology· Volume 68· Issue 3-4
Publisher page

Abstract

Abstract The energy release rates associated with crack growth in multilayered double cantilever beam (DCB), three-point end notched flexure (ENF), and mixed-mode bending (MMB) specimens, including the effects of residual thermal stresses, are derived as special cases of Nairn’s formulation [Nairn JA. On the calculation of energy release rates for cracked laminates with residual stresses. Int J Fract 2006;139:267–93]. The difference between the true toughness and apparent toughness attributable to the consequence of ignoring residual stresses can be calculated for a given specimen geometry and mechanical properties based on classical lamination theory. The true fracture toughness is obtainable using the apparent fracture toughness and the present correction method. Numerical examples of DCB, ENF, and MMB tests are presented, and the calculated difference in the energy release rates based on the present correction method is compared to those obtained using FEM to verify the correction method.
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Research context

OpenAlex topics: Mechanical Behavior of Composites · Fatigue and fracture mechanics · Numerical methods in engineering

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References (25)

Show source-provided references
1. Robinson MJ. Composite cryogenic propellant tank development. AIAA Paper 94-1375-CP.
2. Aoki T, Ishikawa T, Kumazawa H, Morino Y. Mechanical performance of CF/polymer composite laminates under cryogenic conditions. AIAA Paper 2000-1605.10.2514/6.2000-1605 ↗
3. Analysis and experiment of gas leakage through cross-ply laminates for propellant tanks10.2514/2.1895 ↗
4. On initiation and growth of debonding between liner and FW layer of cryogenic composite material tank for rocket system due to nonuniform liner thickness10.6089/jscm.32.237 ↗
5. Mode-I fracture toughness of an adhesively bonded composite–composite joint in a cryogenic environment10.1016/j.compscitech.2006.08.026 ↗
6. On the calculation of energy release rates for cracked laminates10.1007/BF00017790 ↗
7. A test specimen for determining the fracture resistance of bimaterial interfaces10.1115/1.3176069 ↗
8. Prediction of energy release rate for mixed-mode delamination using classical plate theory10.1115/1.3120829 ↗
9. Experimental determination of interfacial toughness using Brazil-nut-sandwich10.1016/0956-7151(90)90200-Z ↗
10. Mixed mode cracking in layered materials10.1016/S0065-2156(08)70164-9 ↗
11. A modified DCB specimen for mode I testing of multidirectional laminates10.1177/002199839202601101 ↗
12. Mode I, mode II, and mixed mode interlaminar fracture of woven fabric carbon/epoxy
13. An Unsymmetric end-notched flexure test for interfacial fracture toughness determination10.1016/S0013-7944(98)00017-4 ↗
14. ASTM D5528 · 2006
15. JIS K7086 · 2004
16. ASTM D6671 · 2006
17. Fracture tests on structural adhesive joints
18. Measurement of interfacial fracture toughness under combined mechanical and thermal stresses10.1115/1.2792645 ↗
19. Energy release rate analysis for adhesive and laminate double cantilever beam specimens emphasizing the effect of residual stresses10.1016/S0143-7496(99)00016-0 ↗
20. Effect of residual stress on the energy release rate of wedge and DCB test specimens10.1016/j.ijadhadh.2005.04.002 ↗
21. On the calculation of energy release rates for cracked laminates with residual stresses10.1007/s10704-006-0044-0 ↗
22. Fracture mechanics of composites with residual thermal stresses10.1115/1.2788985 ↗
23. End corrections for orthotropic DCB specimens10.1016/0266-3538(89)90058-4 ↗
24. Adams · 2003
25. A finite element calculation of stress intensity factors by a modified crack closure integral10.1016/0013-7944(77)90013-3 ↗