Progressive damage analysis of composite bolted joints with liquid shim layers using constant and continuous degradation models

Hühne, Christian; Zerbst, A.-K.; Kuhlmann, G.; Steenbock, Christian; Rolfes, Raimund

doi:10.1016/j.compstruct.2009.05.011

Cited by 117 publications

(64 citation statements)

References 11 publications

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“…7 shows the load displacement curves for different friction coefficients. It is well know that an increment in friction coefficient between plates increases the joint strength [28]. The numerical FE model can reproduce this effect observed in experimental tests re ported in literature.…”

Section: Effect Of Friction Coefficientsupporting

confidence: 60%

“…A parametric study was carried out to verify the capability of the FE model to reproduce the influence of friction coefficient and tightening torque observed in experimental results [28,15]. Fig.…”

Section: Effect Of Friction Coefficientmentioning

confidence: 99%

“…Failure criteria that consider out of plane stresses as Hashin [27] have been applied to predict bearing failure in double lap [4,9] and bolted single lap joints [28,29]. These studies have proved the influence of out of plane stresses on bearing strength, however there is a lack of studies that consider both out of plane stresses and non linear shear stress strain relationship.…”

Section: Introductionmentioning

confidence: 99%

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On the prediction of bolted single-lap composite joints

Olmedo

Santiuste

2012

Composite Structures

156

103

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a b s t r a c tA new set of failure criteria to predict composite failure in single lap bolted joints is proposed. The pres ent failure criteria are an extension of Chang Lessard criteria considering a three dimensional stress field and including out of plane failure modes. The advantage with respect to other three dimensional failure criteria is the consideration of non linear shear stress strain relationship. The failure criteria were imple mented in a finite element model and validated through comparison with experiments in literature. Stresses were calculated by a non linear finite element model developed in ABAQUS/Standard which con siders material and geometric nonlinearities. A progressive damage model was implemented in a USDFLD subroutine. The model predicted the effect of secondary bending and tightening torque showing an excel lent agreement with experimental results. Moreover, results were compared with those reported in lit erature using Hashin failure criteria. In addition, a parametric study was carried out to analyse the influence of friction coefficient and tightening torque.

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Section: Effect Of Friction Coefficientsupporting

confidence: 60%

Section: Effect Of Friction Coefficientmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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On the prediction of bolted single-lap composite joints

Olmedo

Santiuste

2012

Composite Structures

156

103

View full text Add to dashboard Cite

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“…Experimental approaches have been widely used for such studies [1][2][3][4][5][6][7][8][9], while numerical simulations of increasing sophistication are enhancing our understanding of the often complex mechanical response. Recently, three-dimensional (3D) finite element (FE) models have been used to capture the non-uniform, through-thickness stress distributions [10][11][12][13][14][15][16][17], and models to predict the onset and growth of material damage have been incorporated [18][19][20][21][22][23][24][25][26]. The majority of these analyses used implicit FE solvers, which generally have difficulties in converging all the way to the ultimate failure point of CBJs [27], mainly due to the complexity of contact definition between bolts and a damaging laminate.…”

Section: Introductionmentioning

confidence: 99%

A three dimensional implicit finite element damage model and its application to single-lap multi-bolt composite joints with variable clearance

Zhou

Nezhad

Chao-zhen

et al. 2015

Composite Structures

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“…They range from 2D models with rigid pins representing the bolt [78,105,106], to 3D solid models with or without damage development in the composite [47,52,72,76,80,103,[107][108][109][110][111] and they include parameters such as bolt pretension, bolt clearance, the effect of countersunk/protruding bolt heads, different failure initiation and damage progression models, by-pass loading, implicit/explicit solution methods etc. This work includes solid models of countersunk single-lap joints, cf.…”

Section: Modelling Of Quasi-static Failurementioning

confidence: 99%

Static and Fatigue Failure of Bolted Joints in Hybrid Composite-Aluminium Aircraft Structures

Kapidžić¹

2015

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The use of fibre composites in the design of load carrying aircraft structures has been increasing over the last few decades. At the same time, aluminium alloys are still present in many structural parts, which has led to an increase of the number of hybrid composite-aluminium structures. Often, these materials are joined at their interface by bolted connections. Due to their different response to thermal, mechanical and environmental impact, the composite and the aluminium alloy parts are subject to different design and certification practices and are therefore considered separately.The current methodologies used in the aircraft industry lack well-developed methods to account for the effects of the mismatch of material properties at the interface.One such effect is the thermally induced load which arises at elevated temperature due to the different thermal expansion properties of the constituent materials. With a growing number of hybrid structures, these matters need to be addressed. The rapid growth of computational power and development of simulation tools in recent years have made it possible to evaluate the material and structural response of hybrid structures without having to entirely rely on complex and expensive testing procedures.However, as the failure process of composite materials is not entirely understood, further research efforts are needed in order to develop reliable material models for the existing simulation tools. The work presented in this dissertation involves modelling and testing of bolted joints in hybrid composite-aluminium structures.The main focus is directed towards understanding the failure behaviour of the composite material under static and fatigue loading, and how to include this behaviour in large scale models of a typical bolted airframe structure in an efficient way. In addition to that, the influence of thermally induced loads on the strength and fatigue life is evaluated in order to establish a design strategy that can be used in the industrial context. The dissertation is divided into two parts. In the first one, the background and the theory are presented while the second one consists of five scientific papers

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Progressive damage analysis of composite bolted joints with liquid shim layers using constant and continuous degradation models

Cited by 117 publications

References 11 publications

On the prediction of bolted single-lap composite joints

On the prediction of bolted single-lap composite joints

A three dimensional implicit finite element damage model and its application to single-lap multi-bolt composite joints with variable clearance

Static and Fatigue Failure of Bolted Joints in Hybrid Composite-Aluminium Aircraft Structures

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