Effects of temperature and stacking sequence on the model interlaminar fracture behavior of composite laminates

H. S. Kim, W. X. Wang, Y. Takao

Research output: Contribution to journalConference article

3 Citations (Scopus)

Abstract

The purpose of the present study was to clarify the effects of temperature and fiber orientation on the Mode I interlaminar fracture toughness, GI (GIC: GI at initiation, GIR: GI at propagation), of carbon/epoxy composite laminates. In our previous study, the conventional double cantilever beam (DCB) tests were performed to investigate the effects of temperature and fiber orientation in CFRP laminates. It was shown that GI was obviously affected by the temperature and fiber orientation. Especially, in case of the specimen with [45//-45] interface, GIR was considerably affected by both failure mechanisms of crack jumping and fiber bridging. Therefore, in the present study, to suppress the effects of crack jumping and fiber bridging occurred in multidirectional laminates, the side notched double cantilever beam (SN-DCB) specimen is used. DCB tests of [22.5//-22.5] and [45//-45] SN-DCB specimens are conducted at three temperatures, that is, -100°C, 25°C and 150°C. GIC was affected by temperature and fiber orientation, obviously and slightly, respectively. In contrast to GIC, GIR was considerably affected by both temperature and fiber orientation.

Original languageEnglish
Pages (from-to)II/-
JournalKey Engineering Materials
Volume183
Publication statusPublished - Jan 1 2000
Event4th International Conference on Fracture and Strength of Solids - Pohang, South Korea
Duration: Aug 16 2000Aug 18 2000

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Laminates
Fiber reinforced materials
Cantilever beams
Composite materials
Temperature
Cracks
Fibers
Carbon fiber reinforced plastics
Fracture toughness
Carbon

All Science Journal Classification (ASJC) codes

  • Materials Science(all)
  • Mechanics of Materials
  • Mechanical Engineering

Cite this

Effects of temperature and stacking sequence on the model interlaminar fracture behavior of composite laminates. / Kim, H. S.; Wang, W. X.; Takao, Y.

In: Key Engineering Materials, Vol. 183, 01.01.2000, p. II/-.

Research output: Contribution to journalConference article

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AB - The purpose of the present study was to clarify the effects of temperature and fiber orientation on the Mode I interlaminar fracture toughness, GI (GIC: GI at initiation, GIR: GI at propagation), of carbon/epoxy composite laminates. In our previous study, the conventional double cantilever beam (DCB) tests were performed to investigate the effects of temperature and fiber orientation in CFRP laminates. It was shown that GI was obviously affected by the temperature and fiber orientation. Especially, in case of the specimen with [45//-45] interface, GIR was considerably affected by both failure mechanisms of crack jumping and fiber bridging. Therefore, in the present study, to suppress the effects of crack jumping and fiber bridging occurred in multidirectional laminates, the side notched double cantilever beam (SN-DCB) specimen is used. DCB tests of [22.5//-22.5] and [45//-45] SN-DCB specimens are conducted at three temperatures, that is, -100°C, 25°C and 150°C. GIC was affected by temperature and fiber orientation, obviously and slightly, respectively. In contrast to GIC, GIR was considerably affected by both temperature and fiber orientation.

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