Advanced Search

Journal Navigation

Journal Home

Subscriptions

Archive

Contact Us

Table of Contents

Sign In to gain access to subscriptions and/or personal tools.
Journal of Composite Materials
This Article
Right arrow Full Text (PDF)
Right arrow References
Right arrow Alert me when this article is cited
Right arrow Alert me if a correction is posted
Services
Right arrow Email this article to a friend
Right arrow Similar articles in this journal
Right arrow Alert me to new issues of the journal
Right arrow Add to Saved Citations
Right arrow Download to citation manager
Right arrowRequest Permissions
Right arrow Request Reprints
Right arrow Add to My Marked Citations
Citing Articles
Right arrow Citing Articles via HighWire
Right arrow Citing Articles via Google Scholar
Right arrow Citing Articles via Scopus
Google Scholar
Right arrow Articles by Kyoung, W.-M.
Right arrow Articles by Jun, S.-M.
Right arrow Search for Related Content
Social Bookmarking
Add to CiteULike   Add to Complore   Add to Connotea   Add to Del.icio.us   Add to Digg   Add to Reddit   Add to Technorati   Add to Twitter  
What's this?

Modeling of Composite Laminates with Multiple Delaminations under Compressive Loading

Woo-Min Kyoung

Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology, 373-1 Kusong-Dong, Yusong-gu, Taejon, 305-701, Korea

Chun-Gon Kim

Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology, 373-1 Kusong-Dong, Yusong-gu, Taejon, 305-701, Korea

Chang-Sun Hong

Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology, 373-1 Kusong-Dong, Yusong-gu, Taejon, 305-701, Korea

Seung-Moon Jun

Agency for Defense Development, Taejon, 305-600, Korea

Multiple delaminations are more realistic damage types in the laminated composite structures. In this study, buckling and postbuckling analysis was conducted for the composite laminates with multiple delaminations under compressive loading. In a nonlinear finite element formulation, the updated Lagrangian description and modified arc-length method were adopted. For a finite element modeling of composite laminates, the eight-node degenerated shell element was used. To avoid the overlapping between delaminated layers, which is a physically inadmissible buckling mode, the contact node pair was defined by use of virtual beam element. It employed constraints at the overlapped region in the load incremental procedure. Using this modeling of multiple delaminations, accurate results were obtained for the buckling and postbuckling behavior of composite laminates. Numerical results showed that multiple delaminations lower buckling loads and load carrying capacities in the postbuckling region.

Key Words: delamination buckling • multiple delaminations • postbuckling behavior • contact analysis • composite laminate

Journal of Composite Materials, Vol. 32, No. 10, 951-968 (1998)
DOI: 10.1177/002199839803201003
Add to CiteULike CiteULike   Add to Complore Complore   Add to Connotea Connotea   Add to Del.icio.us Del.icio.us   Add to Digg Digg   Add to Reddit Reddit   Add to Technorati Technorati   Add to Twitter Twitter    What's this?


This article has been cited by other articles:


Home page
 Journal of Reinforced Plastics and CompositesHome page
S.-F. Hwang and G.-H. Liu
Experimental Study for Buckling and Postbuckling Behaviors of Composite Laminates with Multiple Delaminations
Journal of Reinforced Plastics and Composites, March 1, 2002; 21(4): 333 - 349.
[Abstract] [PDF]