Delamination in cross-ply laminated composite subjected to low-velocity impact

The behaviour of woven-fabric laminated composite plates has been studied under transverse central low-velocity point impact by using a modi®ed Hertz law and a 3D transient ®nite-element analysis code. The in-plane failure behaviour of the composites has been evaluated by means of a failure function based on the Tsai-Hill quadratic failure criterion. The e ect of fabric geometry on the impact behaviour of woven-fabric composites has been studied. For comparison, the impact behaviour of balanced, symmetric, crossply laminates made of unidirectional layers and unidirectional composites has been included. The studies have been carried out with plate dimensions of 150 mmÂ150 mmÂ6 mm for a supported boundary condition. For these studies, incident impact velocities of 3 and 1 m/s and an impactor mass of 50 gm have been used. It is observed that the in-plane failure function is lower for wovenfabric laminates than for crossply laminates, indicating that woven-fabric laminates are more resistant to impact damage.

show abstract

“…Similarly, force at any time`t Át' is calculated by substituting the impactor and plate displacements of the previous time step using Eq. (17).…”

Section: Itmentioning

confidence: 99%

Damage in woven-fabric composites subjected to low-velocity impact

Naik

Sekher

Meduri

2000

Composites Science and Technology

196

View full text Add to dashboard Cite

show abstract

“…Here, 3 Composite plates of dimensions 150 mm Â 150 mm Â 5 mm made of a typical plain weave E-glass-epoxy laminate GLE-12 were used for the experimental studies under transverse central quasi-static loading. Loading was carried out on the clamped specimens at a loading rate of 0.2 mm/min.…”

Section: Damage Analysismentioning

confidence: 99%

Damage Evolution in Woven Fabric Composites: Transverse Static Loading

Naik

Reddy²,

Raju

2003

Journal of Composite Materials

View full text Add to dashboard Cite

Studies have been carried out on the damage evolution in a typical plain weave fabric composite under transverse central static loading. The stress state has been evaluated throughout the composite plate using finite element analysis software. Possible failure of layers because of in-plane stresses and the delamination mode of failure at the interfaces because of interlaminar stresses have been monitored. It has been observed that the damage initiation and propagation is because of in-plane stresses. The shape of the damage is quasi-lemniscate. Experimental studies have been carried out on a typical plain weave fabric E-glass-epoxy laminate. There is a good match between the predicted and the experimentally observed damage shapes and sizes.KEY WORDS: woven fabric composite, plain weave fabric, transverse static loading, in-plane failure.

show abstract

“…The results were used, in turn, to determine the onset and extent of damage [126]. By incorporating appropriate strength-theory-based failure criteria and fracturemechanics-based crack propagation criteria [127][128][129][130][131] into three-dimensional stress analyses (often through finite element codes), the final extent of damage site, especially the delamination area, may be evaluated. This approach in general involves extensive computations and has been limited to simple lay-up configurations, e.g., symmetric cross-ply laminates.…”

Section: 5: Impact Damage In Compositesmentioning

confidence: 99%

Fast Forward Modeling of EMI Responses from Subsurface Metallic Objects and Ambient Environments

Paulsen¹

2006

View full text Add to dashboard Cite

Fonn Approved OMB NO. 0704-0188 PubHc Reporting burden for this collection of infonnation is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gatnering and mainbioing tbe data needed, and completing and reviewing tbe collection of informatiou. Send comment regarding tllis burden estimates or any oHlef aspect of this collection of infonnation, including suggestions for reducing tbis burden, to Washington Headquarters Services, Directorate for infonnatioD Operations and Reports, 1215 Jefferson Davis Highway, Suite l204, Arlin£ton, VA 22202-4302, and to the Office of Mana£ement and Bnd£et, Paperwork Reduction Proiect (0704-0188,\ Washin£ton, DC 20503.

show abstract

Delamination in cross-ply laminated composite subjected to low-velocity impact

Cited by 51 publications

References 4 publications

Damage in woven-fabric composites subjected to low-velocity impact

Damage in woven-fabric composites subjected to low-velocity impact

Damage Evolution in Woven Fabric Composites: Transverse Static Loading

Fast Forward Modeling of EMI Responses from Subsurface Metallic Objects and Ambient Environments

Contact Info

Product

Resources

About