@article{10.11648/j.cm.20220602.11,
  author = {Enock Andrews Duodu},
  title = {Analysis of Damage-Induced on Fiber Reinforced S-Glass Composite Laminate at Low Velocity Loading Condition},
  journal = {Composite Materials},
  volume = {6},
  number = {2},
  pages = {49-58},
  doi = {10.11648/j.cm.20220602.11},
  url = {https://doi.org/10.11648/j.cm.20220602.11},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.cm.20220602.11},
  abstract = {Structural performance of reinforced S-glass composite laminate at low velocity impact loading was investigated with three different impactors to characterize the induced-damage behavior. In this study, a total of 12 samples were tested numerically with three distinct impactors at four different energy thresholds 5-13 J to examine the damage behavior of the reinforced S-glass composite laminate in terms of intra-laminar, inter-laminar and stress failure responses. Dynamic finite element coded ABAQUS/Explicit software through user-written subroutines was used to create the geometry models to capture the impact damage response. A composite laminate plate of diameter 150 mm and thickness 6.5 mm with stacking configuration [90/45/45/0/-45]S was designed together with three different impactor geometrical shapes (spherical, flat cylindrical and conical). The flat cylindrical impactor measures 15 mm radius and 20 mm high; the conical shape length 20 mm, radius 15 mm with a tip-end angle of 112°; while the spherical impactor measures 15 mm in radius. This impactor was modeled as analytical rigid body of mass 1.6 kg with a force of 15.69 N prescribed in transverse direction and composite plate was actuated by surface-to-surface contact pairs within ABAQUS/Explicit platform with penalty enforcement contact method. A relative fine element mesh of 0.1 mm x 0.1 mm was applied on the impact location on the composite laminate with failed interface elements allowed to remain in the model to circumvent penetration of damage layers using an element option platform. A total number of 83640 solid elements, 75276 cohesive elements and 171420 nodes were applied for the simulation. This study discloses that irrespective of impactor profile, damage threshold increases with increase in impact energy level. The dominant damage modes found in the composite laminate are matrix cracking and delamination. The study also shows better correlation among the models for damage area responses and that flat head impactor exhibits largest delamination area compared to spherical and conical edge impactors. The study shows that stress value on the conical edge impactor is greater on the impacted layer and lesser on the bottom layer amongst the impactors due to geometrical profile. Comparison amongst the models raises the necessity to incorporate energy distortion criterion into this constitutive damage model. It is therefore recommended to engineers and researchers to adapt this model to improve and optimize the design processes of composite materials in the automobile and aviation structural applications.},
 year = {2022}
}

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TY  - JOUR
T1  - Analysis of Damage-Induced on Fiber Reinforced S-Glass Composite Laminate at Low Velocity Loading Condition
AU  - Enock Andrews Duodu
Y1  - 2022/10/29
PY  - 2022
N1  - https://doi.org/10.11648/j.cm.20220602.11
DO  - 10.11648/j.cm.20220602.11
T2  - Composite Materials
JF  - Composite Materials
JO  - Composite Materials
SP  - 49
EP  - 58
PB  - Science Publishing Group
SN  - 2994-7103
UR  - https://doi.org/10.11648/j.cm.20220602.11
AB  - Structural performance of reinforced S-glass composite laminate at low velocity impact loading was investigated with three different impactors to characterize the induced-damage behavior. In this study, a total of 12 samples were tested numerically with three distinct impactors at four different energy thresholds 5-13 J to examine the damage behavior of the reinforced S-glass composite laminate in terms of intra-laminar, inter-laminar and stress failure responses. Dynamic finite element coded ABAQUS/Explicit software through user-written subroutines was used to create the geometry models to capture the impact damage response. A composite laminate plate of diameter 150 mm and thickness 6.5 mm with stacking configuration [90/45/45/0/-45]S was designed together with three different impactor geometrical shapes (spherical, flat cylindrical and conical). The flat cylindrical impactor measures 15 mm radius and 20 mm high; the conical shape length 20 mm, radius 15 mm with a tip-end angle of 112°; while the spherical impactor measures 15 mm in radius. This impactor was modeled as analytical rigid body of mass 1.6 kg with a force of 15.69 N prescribed in transverse direction and composite plate was actuated by surface-to-surface contact pairs within ABAQUS/Explicit platform with penalty enforcement contact method. A relative fine element mesh of 0.1 mm x 0.1 mm was applied on the impact location on the composite laminate with failed interface elements allowed to remain in the model to circumvent penetration of damage layers using an element option platform. A total number of 83640 solid elements, 75276 cohesive elements and 171420 nodes were applied for the simulation. This study discloses that irrespective of impactor profile, damage threshold increases with increase in impact energy level. The dominant damage modes found in the composite laminate are matrix cracking and delamination. The study also shows better correlation among the models for damage area responses and that flat head impactor exhibits largest delamination area compared to spherical and conical edge impactors. The study shows that stress value on the conical edge impactor is greater on the impacted layer and lesser on the bottom layer amongst the impactors due to geometrical profile. Comparison amongst the models raises the necessity to incorporate energy distortion criterion into this constitutive damage model. It is therefore recommended to engineers and researchers to adapt this model to improve and optimize the design processes of composite materials in the automobile and aviation structural applications.
VL  - 6
IS  - 2
ER  - 

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