journal article·2007-01

Suppression of interfacial crack for foam core sandwich panel with crack arrester

Y. Hirose, M. Hojo, A. Fujiyoshi, G. Matsubara

Advanced Composite Materials· Volume 16· Issue 1
Publisher page

Abstract

Abstract Since delamination often propagates at the interfacial layer between a surface skin and a foam core, a crack arrester is proposed for the suppression of the delamination. The arrester has a semi-cylindrical shape and is arranged in the foam core and is attached to the surface skin. Here, energy release rates and complex stress intensity factors are calculated using finite element analysis. Effects of the arrester size and its elastic moduli on the crack suppressing capability are investigated. Considerable reductions of the energy release rates at the crack tip are achieved as the crack tip approached the leading edge of the crack arrester. Thus, this new concept of a crack arrester may become a promising device to suppress crack initiation and propagation of the foam core sandwich panels. Keywords: FOAM CORESANDWICH STRUCTURENEW CRACK ARRESTERDELAMINATION SUPPRESSIONFRACTURE MECHANICSENERGY RELEASE RATE
Source: openalex_inverted_index · Quality: baseline

Research context

OpenAlex topics: Mechanical Behavior of Composites · Cellular and Composite Structures · Structural Analysis of Composite Materials

SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.

References (19)

Show source-provided references
1. Fawcett, A., Trostle, J. and Ward, S. 777 empennage certification approach. Proc. ICCM11. Gold Coast, Australia. pp.178–199.
2. Schulz, D. Structural certification of Airbus fin box in composite fiber construction. Proc 14th International Congress of Aerospace Sciences. Toulouse, France. pp.427–438.
3. Ochi, S., Hirose, Y., Nishitani, M., Sana, T., Ito, T., Ikeda, Y. and Kikukawa, H. Development of CFRP sandwich panel structure for transport nose component. Proc. 9th European?Japanese Symposium on Composite Materials. Hamburg, Germany.
4. Ikeda, Y., Hirose, Y., Nishitani, M., Ochi, S. and Ito, T. Development of foam core sandwich panel structure for transport nose structure. Proc. 5th Gyeongnam (Korea)-Tokai (Japan) Aerospace Technology Symposium. Sacheon, Korea. pp.67–78.
5. Herbec, L. Technology and design development for a CFRP fuselage. Presented at 25th SAMPE Europe Conference. Paris, France.
6. Bruman M. · 1998
7. Shipsha A. · 2001
8. Hirose, Y., Konishi, M., Kosugi, K., Imuta, M. and Kikukawa H, H. Industrial application of CFRP sandwich panel for aircraft structure. Proc. Conference ICCM/8. Tenerife, Canary Island, Spain. pp.355–356.
9. Hellbrantt, S.E. Experience from design and production of the 72 m CFRP-sandwich corvette Visby. Proc.6th International Conf. Sandwich Struct. Ft. Lauderdale, Florida. pp.15–24.
10. Hirose, Y., Kosugi, K., Nishitani, M., Sashikuma, H., Imuta, M., Fukagawa, H. and Kukukawa, H. The CFRP sandwich panel for aircraft nose structure. Proc. 23rd Int. Congress Aerospace Sci. Toronto, Canada. pp.343.1–343.10.
11. Hirose, Y., Fukagawa, H., Kosugi, K., Imuta, M. and Kikukawa, H. Application of a new CFRP sandwich panel to the aircraft nose structure. Proc. 10th US?Japan Conf. Compos. Mater. pp.969–977. USA: Stanford University.
12. Yuki, T., Kishimoto, K. and Shu, J. 1993.Mechanics of Interface, 91–96. Tokyo: Baifukan Co., LTD.
13. Ikeda T. · Engng Fract. Mech. · 1998 · 59 · 72510.1016/S0013-7944(97)00177-X ↗
14. Ikeda T. · Int. J. Fract. · 2001 · 111 · 22910.1023/A:1012208409795 ↗
15. Qian W. · Compos. Sci. Technol. · 1997 · 57 · 63710.1016/S0266-3538(97)00006-7 ↗
16. Matsushita Y. · 2005
17. Ryubicki E. F. · Eng. Fract. Mech. · 1977 · 9 · 93110.1016/0013-7944(77)90013-3 ↗
18. Prasad S. · Engng. Fract. Mech. · 1994 · 47 · 81310.1016/0013-7944(94)90061-2 ↗
19. Prasad S. · Engng. Fract. Mech. · 1994 · 47 · 82510.1016/0013-7944(94)90062-0 ↗