by National Aeronautics and Space Administration, Langley Research Center, National Technical Information Service, distributor in Hampton, Va, [Springfield, Va .
Written in English
|Series||NASA contractor report -- 187594., NASA contractor report -- NASA CR-187594.|
|Contributions||Langley Research Center.|
|The Physical Object|
Analysis of delamination in cross-ply laminates initiating from impact induced matrix cracking. indicating that matrix cracking may give rise to delamination. The ratio of Mode I to total strain energy release rate, G(I)/G(total), at the beginning of delamination, calculated at the two (top and bottom) matrix crack tips was 60 and 28 Author: S. A. Salpekar. Delamination in cross-ply laminated composite subjected to low-velocity impact. Matrix crack interacting with a delamination in an impacted sandwich composite beam. The finite element analysis of impact induced delamination in composite materials using Cited by: According to the nature of cross-ply laminates, transverse cracking is not, however, sufficient for describing the development of transverse cracks in 90° plies in the case of monotonic loading. In this case, the delamination process induced at transverse crack tips is to be considered for describing the experimental by: In this paper, a constitutive model of the damage state for composite laminates, first proposed by Allen et al., is used with a damage evolution criterion based on strain energy to predict the stiffness loss due to matrix cracking in cross-ply laminated composite plates. Although the constitutive model does not require the determination of many.
Composite laminate has extensive usage in the aerospace and automotive industries. Thus delamination, one of its most prevalent and challenging failure modes, has attracted substantial research. For cross-ply laminates under quasi-static loading, fast fracture or crack onset (rapid growth) of the cracks usually occurs when the applied load (or strain) is typically %; for thin transverse plies (i.e., thicknesses typically ≤ mm), the onset strain for matrix cracking can be delayed. Figure (a) shows a typical tensile stress–stain curve for a cross-ply laminate; the. Nonlinear and First-Ply Failure Analyses of Laminated Composite Cross-Ply Plates Show all authors by the adopted failure criteria indicate that the strength-of-material approach may be inappropriate for the first-ply failure analysis of laminated composite plates. "Analysis of Progressive Matrix Cracking in Composite Laminates II: First. Fiber Reinforced Polymer (FRP) laminates have properties, which are highly dependent on the ply fiber orientations and which can be designed for optimum laminate performance. The purpose of this study is to investigate the effect of matrix cracking on the mechanical properties of FRP laminates with various off-axis angles, and to provide a critical test for an analytical solution using.
The present paper is devoted to development of such tools geared toward laminated composite applications. Matrix cracking and delamination initiation, propagation, and interaction prediction in. The impact damage mechanism in a laminate constitutes a very complex process. It is a combination of matrix cracking, surface buckling, delamination, fiber shear-out, and fiber fracture, etc., which usually all interact with each other. In this paper, a numerical method was developed to simulate matrix cracking and splitting in addition to induced delamination and fibre breakage that occur in a cross-ply laminate when subjected to impact loading. Existing damage criteria were implemented into the user subroutine VUMAT of the commercially available FE code Abaqus/Explicit. Analysis of delamination in cross-ply laminates initiating from impact induced matrix cracking development due to an impact load. A cross section through the thickness of the laminate with.