Crack Deflection Near a Ply Interface in a Composite Laminate Conference Paper uri icon


  • Abstract The deflection of a matrix crack near 0/90 interface in a cross-ply laminate was studied numerically. In the finite element (FE) model, an initial matrix crack was introduced in the 90 layers away from the 0/90 interface. The initial matrix crack could be initiated either at the middle of 90 layer or at one side of 0/90 interface. The 0 layers and a part of the initial matrix crack were modeled using homogenized layer properties to simplify the model. The nonuniformly distributed fibers were modeled explicitly close to the 0/90 interface in order to study the influence of this nonuniformity on the crack deflection process. The Energy Release Rate (ERR) of debond crack tip was calculated using Virtual Crack Closure Technique (VCCT) to study the debond growth. Maximum principal stress was then adopted to access the debond crack kinking qualitatively. Its found that when a macro-size matrix crack forms and propagate towards ply interface, the subsequent debonding and debond cracking process in nearby intact fiber shows some distinct differences compared to the same processes at single isolated fiber without considering the interaction with nearby debonded fiber and existing matrix crack. Meanwhile, present analysis shows clear influence of microstructures on the crack deflection process by affecting the fiber/matrix debonding and debond kinking processes.

name of conference

  • Volume 4: Advances in Aerospace Technology

published proceedings

  • Volume 4: Advances in Aerospace Technology

author list (cited authors)

  • Zhuang, L., Talreja, R., & Maragoni, L.

citation count

  • 0

complete list of authors

  • Zhuang, Linqi||Talreja, Ramesh||Maragoni, Lucio

publication date

  • January 2020