Upscaling from a micro-mechanics model to capture laminate compressive strength due to kink banding instability

Prabhakar, Pavana; Waas, Anthony M.

doi:10.1016/j.commatsci.2012.08.025

Cited by 27 publications

(12 citation statements)

References 22 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…These include cohesive zone modelling (21)(22)(23)(24) , modelling notched strength (6,(25)(26)(27)(28)(29) , compressive failure (30,31) , flexural response of textiles (32,33) , and transverse cracking (34) . In addition, several micromechanics-based models provide insights on capturing experimental observations and providing mechanical properties that can be used for up-scaling in structural level calculations (28,(35)(36)(37)(38) . While several other papers address various aspects of ICME of FRPCs and ceramic matrix composites (39) , this paper focuses on the specific topic of cure-induced effects on subsequent mechanical response of FRPCs.…”

Section: Introductionmentioning

confidence: 99%

Virtual manufacturing of composite aerostructures

2016

View full text Add to dashboard Cite

The past century has witnessed the rise and maturity of the flying machine, starting with the Wright brothers flyer to today's modern passenger aircrafts and warfighters. At the start of this century, yet another achievement in flying vehicle technology was seen with the launch of the Boeing 787 aircraft, which has a significant portion by weight of polymer matrix fibre composites. This paper, therefore, addresses the effects of the manufacturing process of fibre reinforced polymer matrix composites on mechanical performance. Computations are carried out using the Finite Element (FE) method at the microscale where Representative Volume Elements (RVEs) are analysed with Periodic Boundary Conditions (PBCs). Straight fibre prepreg-based composites and textile composites are considered. The commercial code ABAQUS is used as the solver for the FE equations, supplemented by user-written subroutines. The transition from a continuum to damage/failure is effected by using the Bažant-Oh crack band model, which preserves mesh objectivity. Results are presented for RVEs that are first subjected to curing and subsequently to mechanical loading. The effect of the fibre packing randomness on the microstructure is examined by considering multifibre RVEs where fibre volume fraction is held constant but with random packing of fibres. Plain weave textile composites are also cured first and then subjected to mechanical loads. The possibility of failure is accommodated throughout the analysis -failure can take place during the curing process even prior to the application of in-service mechanical loads. The analysis shows the differences in both the cured RVE strength and stiffness, when cure-induced damage has and has not been taken into account.

show abstract

Section: Introductionmentioning

confidence: 99%

Virtual manufacturing of composite aerostructures

2016

View full text Add to dashboard Cite

show abstract

“…-45 0 ,45 0 ,90 0 layers, are homogenized using the technique mentioned in Prabhakar and Waas. 24 Here, the red, cream and blue regions are the homogenized -45, +45 and 90 degree laminae. Micro-mechanics is maintained in the 0 0 layers, as they are the load bearing layers and are responsible for kink band formation in multi-directional laminates.…”

Section: A Upscaled Laminate Modelmentioning

confidence: 99%

“…Upscaled models of homogenized laminates are constructed for two different layups, with stacking of [(−45 2 /+45 2 /90 2 /0 2 )] s (Type A) and [(−45/+45/90/0) 2 ] s (Type B) as explained in Prabhakar and Waas,24 where the 0 degree layers have a hexagonal packed fibers maintaining the micro-mechanics, and the off-axis layers are homogenized using Hill's anisotropic plasticity along with deformation theory of plasticity. Interface discrete cohesive zone method (DCZM) elements are added at critical interfaces which are determined a priori.…”

Section: Computational Modelingmentioning

confidence: 99%

Failure Mode Predictions in the Compressive Response of Laminated Composites

Prabhakar¹,

Waas²

2013

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

Self Cite

View full text Add to dashboard Cite

Of interest in this paper are failure mode interactions when laminated fiber reinforced composites are subjected to compressive loading. Delamination, fiber kink-banding and their interactions are seen to dominate the failure response. This interaction is captured through a computational model that includes interface elements to capture delamination, and, geometric and material nonlinearity to capture kink banding. A 2D cross-section analysis is used to guide the choice of interfaces that require cohesive elements, thus reducing computational complexity. Two different stacking sequences are investigated, and their compressive strength and failure modes are compared, between prediction and experiments.

show abstract

“…24 The 0 degree laminae have hexagonal packed fibers maintaining the micro-mechanics, and the off-axis layers are homogenized using a deformation theory implementation of Hill's anisotropic plasticity theory. Interface elements formulated using the discrete cohesive zone method (DCZM), 25 are added at the interface between -45/+45 layers, which is determined a priori as the weakest interface in the laminate.…”

Section: Computational Modelingmentioning

confidence: 99%

“…-45 0 ,45 0 ,90 0 layers are homogenized using the technique mentioned in. 24 Here, the red, cream and blue regions are the homogenized -45, +45 and 90 degree laminae. Micro-mechanics is maintained in the 0 0 layers, as they are the load bearing layers and are responsible for kink band formation in multi-directional laminates.…”

Section: A Upscaled Laminate Modelmentioning

confidence: 99%

The Interaction of Failure Modes in the Compression Response and Failure of Laminated Composites

Prabhakar¹,

Waas²,

Raveendra

2012

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials ConferenceSelf Cite

4
0
1
0

View full text Add to dashboard Cite

Failure mode interactions when a laminated fiber reinforced composite is subjected to compression is studied here. Delamination, fiber kink-banding and their interaction are seen to dominate the failure response. An upscaled semi-homogenized laminate model is developed to predict the observed compression response of multi-directional laminates. A reduced 2-D formulation is presented first to determine the interfaces most susceptible to delamination. Subsequently, cohesive elements are added along these interfaces to introduce delamination capability in the model. Predictions of the model are compared against experimental data, and are found to be in agreement with respect to compressive strength and failure modes.

show abstract

Upscaling from a micro-mechanics model to capture laminate compressive strength due to kink banding instability

Cited by 27 publications

References 22 publications

Virtual manufacturing of composite aerostructures

Virtual manufacturing of composite aerostructures

Failure Mode Predictions in the Compressive Response of Laminated Composites

The Interaction of Failure Modes in the Compression Response and Failure of Laminated Composites

Contact Info

Product

Resources

About