Damage tolerance of laminated tee joints in FRP structures

Phillips, Holly; Shenoi, R.A.

doi:10.1016/s1359-835x(97)00081-x

Cited by 54 publications

(26 citation statements)

References 15 publications

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“…The literature survey of T-joints shows that filler region and flange tips are the critical locations for delamination/debond initiation. Two of the major initiation mechanisms observed in the literature are the debond of the filler/stringer interface [10,19,23] as shown in Figure 3 and the delamination of plies in the stringer laminate at the curved region [1,3,4,6] as shown in Figure 4. …”

Section: Critical Regions In T-joints For Delamination/debondmentioning

confidence: 99%

“…Under various loading conditions (mechanical, buckling, cyclic, hydrothermal, low velocity impact, bird strike, underwater explosion, lightning, etc. [2,3,4,5,14,21]), interlaminar normal and shear stresses are generated between the composite plies in these critical regions which cause delaminations/debonds. Delamination/debond reduces the stiffness and strength of the structure as the delaminated area gets larger.…”

Section: Introductionmentioning

confidence: 99%

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Delamination-Debond Behaviour of Composite T- Joints in Wind Turbine Blades

Gülaşık¹,

Çöker²

2014

J. Phys.: Conf. Ser.

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Abstract. Wind turbine industry utilizes composite materials in turbine blade structural designs because of their high strength/stiffness to weight ratio. T-joint is one of the design configurations of composite wind turbine blades. T-joints consist of a skin panel and a stiffener co-bonded or co-cured together with a filler material between them. T-joints are prone to delaminations between skin/stiffener plies and debonds between skin-stiffener-filler interfaces. In this study, delamination/debond behavior of a co-bonded composite T-joint is investigated under 0° pull load condition by 2D finite element method. Using Abaqus ® commercial FE software, zero-thickness cohesive elements are used to simulate delamination/debond in ply interfaces and bonding lines. Pulling load at 0° is applied and load-displacement behavior and failure scenario are observed. The failure sequence consists of debonding of filler/stringer interface during one load drop followed by a second drop in which the 2 nd filler/stringer debonds, filler/skin debonding and skin delamination leading to total loss of load carrying capacity. This type of failure initiation has been observed widely in the literature. When the debond strength is increased 30%, failure pattern is found to change in addition to increasing the load capacity by 200% before total loss of loading carrying capacity occurs. Failure initiation and propagation behavior, initial and max failure loads and stress fields are affected by the property change. In all cases mixed-mode crack tip loading is observed in the failure initiation and propagation stages. In this paper, the detailed delamination/debonding history in T-joints is predicted with cohesive elements for the first time.

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Section: Critical Regions In T-joints For Delamination/debondmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Delamination-Debond Behaviour of Composite T- Joints in Wind Turbine Blades

Gülaşık¹,

Çöker²

2014

J. Phys.: Conf. Ser.

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“…Many papers are investigated on the single composite skin T-joints and their improvement [4][5][6][7][8][9][10][11][12][13]. The T-joint connections can have fillers or fillets with no overlaminate as well as thin or thick overlaminates of small or large radius of curvature [14].…”

mentioning

confidence: 99%

“…A tension load to the leg panel in the presence of a disbond caused the overlaminate to deform such that it would tend to cause the disbond to grow. Also, Shenoi et al [13] studied the effect of separating overlaminate layers with finite element method (FEM). They used an iterative procedure to characterize the damage which occurs in tee joints under a three point bending loading.…”

mentioning

confidence: 99%

“…In the most of previous numerical studies [5][6][7][8][9][10][11][12][13][14][15][16][17][18]20], adhesive failure, propagation of cracks in the adhesive and separation of joint elements or core shear failure are not modeled, so their analysis are not able to model the fracture modes or are not able to anticipate maximum failure load. On the other hand, the foam which is used by Toftegaard and Lystrup [14] had low shear strength.…”

mentioning

confidence: 99%

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Behavior and Failure Modes of Sandwich T-Joint Using Cohesive Zone Material Model and Contact Elements

Khalili

Ghaznavi

2012

Appl Compos Mater

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One of the significant concerns of sandwich panels is their joints. T-joint is one the most common joint in sandwich structures. This paper deals with the numerical study of triangle T-joint under static loading. The results of numerical solution obtained by ANSYS modeling are verified with the results of experimental tests obtained in the literature. In general, the results obtained for anticipated failure load by numerical solution with the results of experimental test is in good agreement. Contact elements and cohesive zone material model are used to model the adhesive layer, hence debonding and fracture of adhesive is observed by the numerical modeling. Also, by using a written macro code in the ANSYS software, the ability of damage is explained for the core of sandwich panels; thus both the modes in fracture of T-joints (core shear failure in base panel and debonding of adhesive) are modeled. Core materials consist of Divinycell H100, H160, H250, and HCP70 are used for modeling sandwich panels, so that the function of joint is studied under different conditions of the sandwich core material. Nine different geometrical models are created by changing the base angle of the core triangle. The absorbed energy associated with different segments of the T-joint are used to investigate the effect of joint geometry and core material on the load transfer and failure mode of the T-joint.

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