This study demonstrates a homogenization approach via a modified state-based peridynamic(PD)method to predict the effective elastic properties of composite materials with periodic microstructure.The procedure of model...This study demonstrates a homogenization approach via a modified state-based peridynamic(PD)method to predict the effective elastic properties of composite materials with periodic microstructure.The procedure of modeling the PD unit cell(UC)of continuous fiber-reinforced composite is presented.Periodic boundary conditions are derived and implemented through the Lagrange multiplier method.A matrix-dominated approach for modeling the interphase properties between dissimilar materials is proposed.The periodicity and continuity assumptions are employed to determine the stress and strain fields,as well as the effective elastic properties.The PD-UCs of square and hexagonal packs as well as the 0/90 laminate microstructure are modeled and compared with the analytical,numerical and experimental results from the literature.Good agreement of predicted effective properties can be observed.Unlike other PD homogenization approaches,the effective material properties can be directly and individually obtained from simple loading conditions.展开更多
The progressive failure in the top-hat stiffened composite panel under four-point bending damage was analyzed.The cohesive element was applied to simulate the debonding between the fuselage skin and stringer.In additi...The progressive failure in the top-hat stiffened composite panel under four-point bending damage was analyzed.The cohesive element was applied to simulate the debonding between the fuselage skin and stringer.In addition,the quadratic stress criterion and B–K criterion were adopted to predict initiation and propagation of the debondings.The propagation process,failure mode and ultimate load of the stiffened composite panel under four-point bending were predicted and compared with the test results.Specimens with co-bonded and co-cured processes were considered in this study.In regard to the co-bonded specimens,there existed only delamination between skin and stringer.The error between the predicted and experimental results of debonding load was about 2–8.8%.In terms of the co-cured specimens,the debonding between skin and stringer and the intra-layer cracks both can be observed.展开更多
基金This work is supported by the National Natural Science Foundation of China under Grant Nos.1190219711972234 and is sponsored by Shanghai Sailing Program under Contract No.19YF1421700.
文摘This study demonstrates a homogenization approach via a modified state-based peridynamic(PD)method to predict the effective elastic properties of composite materials with periodic microstructure.The procedure of modeling the PD unit cell(UC)of continuous fiber-reinforced composite is presented.Periodic boundary conditions are derived and implemented through the Lagrange multiplier method.A matrix-dominated approach for modeling the interphase properties between dissimilar materials is proposed.The periodicity and continuity assumptions are employed to determine the stress and strain fields,as well as the effective elastic properties.The PD-UCs of square and hexagonal packs as well as the 0/90 laminate microstructure are modeled and compared with the analytical,numerical and experimental results from the literature.Good agreement of predicted effective properties can be observed.Unlike other PD homogenization approaches,the effective material properties can be directly and individually obtained from simple loading conditions.
基金supported by National Natural Science Foundation of China under Grant Nos.U2241266,11902197 and 11972234.
文摘The progressive failure in the top-hat stiffened composite panel under four-point bending damage was analyzed.The cohesive element was applied to simulate the debonding between the fuselage skin and stringer.In addition,the quadratic stress criterion and B–K criterion were adopted to predict initiation and propagation of the debondings.The propagation process,failure mode and ultimate load of the stiffened composite panel under four-point bending were predicted and compared with the test results.Specimens with co-bonded and co-cured processes were considered in this study.In regard to the co-bonded specimens,there existed only delamination between skin and stringer.The error between the predicted and experimental results of debonding load was about 2–8.8%.In terms of the co-cured specimens,the debonding between skin and stringer and the intra-layer cracks both can be observed.
