CaltechAUTHORS
  A Caltech Library Service

Scaling global fracture behavior of structures-sized laminated composites

Gonzáles, Luis and Knauss, Wolfgang G. (2002) Scaling global fracture behavior of structures-sized laminated composites. International Journal of Fracture, 118 (4). pp. 363-394. ISSN 0376-9429. doi:10.1023/a:1023351115322. https://resolver.caltech.edu/CaltechAUTHORS:20191008-142521434

Full text is not posted in this repository. Consult Related URLs below.

Use this Persistent URL to link to this item: https://resolver.caltech.edu/CaltechAUTHORS:20191008-142521434

Abstract

The propagation of damage in laminated fiber composites similar to a crack-like configuration is studied experimentally. Of particular interest is the behavior of a ‘macro-crack' or ‘global crack' that propagates through a large scale structure (e.g., airplane fuselage or wing) with the potential interaction of stringers or other reinforcements. The question is considered whether such damage propagation can be understood in terms of classical fracture mechanics. Because the damage zone (wake width) can be very extensive and may be measured in terms of inches, the question arises as to the scalability of associated ‘fracture' phenomena. An integral part of this investigation is thus an examination of the size of the test specimens to establish whether a minimum size is required to relate fracture at larger scales by laboratory specimens. Using (globally anisotropic) 32-lamina composite specimens, proportioned like compact tension specimens, it is found that test ‘coupons' on the order of 45 to 50 cm on a side (18×18 in.^2) or larger are needed to begin simulating large scale structures for establishing a global equivalent of a fracture energy for ‘crack propagation' simulations. Displacement controlled tests on groups of three specimen sizes (15, 30 and 46 cm on a side) indicate that scaling can be accomplished through the square root of the linear specimen or crack dimension. In certain lay-ups ‘run-away delamination' severs the surface laminae so that the reinforcement action of stringers is jeopardized. Damage at the `global crack front' is quantified through an effective area relation, with a characteristic value for the mostly intra-laminar initiation of damage (intra-lamina cracks) at a sharp notch, and another value conceived of as governing the onset of unstable growth.


Item Type:Article
Related URLs:
URLURL TypeDescription
https://doi.org/10.1023/a:1023351115322DOIArticle
https://rdcu.be/bTAzlPublisherFree ReadCube access
Additional Information:© 2002 Kluwer Academic Publishers. Received 8 August 2002; accepted in revised form 24 January 2003. This work was performed in part with support from NASA under grants NAG-1-1975 and NAG-1-02029. The authors are grateful for discussions with and the enduring encouragement by the former technical monitor, Dr. James Starnes.
Group:GALCIT
Funders:
Funding AgencyGrant Number
NASANAG-1-1975
NASANAG-1-02029
Subject Keywords:Global fracture behavior; laminated composites
Issue or Number:4
DOI:10.1023/a:1023351115322
Record Number:CaltechAUTHORS:20191008-142521434
Persistent URL:https://resolver.caltech.edu/CaltechAUTHORS:20191008-142521434
Official Citation:Gonzáles, L. & Knauss, W.G. International Journal of Fracture (2002) 118: 363. https://doi.org/10.1023/A:1023351115322
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:99162
Collection:CaltechAUTHORS
Deposited By: Tony Diaz
Deposited On:08 Oct 2019 21:35
Last Modified:16 Nov 2021 17:44

Repository Staff Only: item control page