Progressive damage analysis of multi-bolt composite joints with variable bolt–hole clearances

McCarthy, Conor T.; McCarthy, Michael A.; Lawlor, V.

doi:10.1016/j.compositesb.2004.11.003

Cited by 197 publications

(127 citation statements)

References 30 publications

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“…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: Introductionmentioning

confidence: 99%

“…The bolting parameters that have been studied include geometric factors [10], material properties [11], coefficients of fric tion [12], bolt shape [13], clearance [9], and torque [14,15]. These studies have provided strategies to design composite bolted joints avoiding catastrophic failure.…”

Section: Introductionmentioning

confidence: 99%

On the prediction of bolted single-lap composite joints

Olmedo

Santiuste

2012

Composite Structures

156

103

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“…MPDM schemes are often implemented through userdefined subroutines (Chen et al, 1999;Xiao and Ishikawa, 2002;Goswami, 2005;McCarthy et al, 2005;Basu et al, 2007). Credited with being the first in this direction, Chang and Chang (1987) developed a composite laminate in tension with a circular hole where material properties were degraded to represent damage.…”

Section: Continuum Damage Modeling Backgroundmentioning

confidence: 99%

Effects of defects in composite wind turbine blades – Part 2: Progressive damage modeling of fiberglass-reinforced epoxy composites with manufacturing-induced waves

Nelson

Riddle²,

Cairns

2017

Wind Energ. Sci.

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Abstract. Composite wind turbine blades are typically reliable; however, premature failures are often in regions of manufacturing defects. While the use of damage modeling has increased with improved computational capabilities, they are often performed for worst-case scenarios in which damage or defects are replaced with notches or holes. To better understand and predict these effects, an effects-of-defects study has been undertaken. As a portion of this study, various progressive damage modeling approaches were investigated to determine if proven modeling capabilities could be adapted to predict damage progression of composite laminates with typical manufacturing flaws commonly found in wind turbine blades. Models were constructed to match the coupons from, and compare the results to, the characterization and material testing study presented as a companion. Modeling methods were chosen from established methodologies and included continuum damage models (linear elastic with Hashin failure criteria, user-defined failure criteria, nonlinear shear criteria), a discrete damage model (cohesive elements), and a combined damage model (nonlinear shear with cohesive elements). A systematic, combined qualitative-quantitative approach was used to compare consistency, accuracy, and predictive capability for each model to responses found experimentally. Results indicated that the Hashin and combined models were best able to predict material response to be within 10 % of the strain at peak stress and within 10 % of the peak stress. In both cases, the correlation was not as accurate as the wave shapes were changed in the model; correlation was still within 20 % in many cases. The other modeling approaches did not correlate well within the comparative framework. Overall, the results indicate that this combined approach may provide insight into blade performance with known defects when used in conjunction with a probabilistic flaw framework.

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“…Some examples are laminate type, friction [44], secondary bending and bolt tilting [45,46], amount of by-pass and bearing load [47], fastener type (countersunk or protruding head) [31-33, 36, 48, 49], load transfer [50], pretension, [51], clearance [52][53][54] etc. Most of the studies were performed on specimens with only a few bolts and in some cases only one.…”

Section: Bolted Jointsmentioning

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 multi-bolt composite joints with variable bolt–hole clearances

Cited by 197 publications

References 30 publications

On the prediction of bolted single-lap composite joints

On the prediction of bolted single-lap composite joints

Effects of defects in composite wind turbine blades – Part 2: Progressive damage modeling of fiberglass-reinforced epoxy composites with manufacturing-induced waves

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

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