Effect of secondary bending on strength prediction of composite, single shear lap joints

Ekh, Johan; Schön, Joakim

doi:10.1016/j.compscitech.2004.10.020

Cited by 45 publications

(22 citation statements)

References 33 publications

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“…As it is well known, damage indicators are dependent on stress fields, and thus critical values of stresses should be limited to ensure damage absence. Table 4 summarizes the most significant values of stresses in the bolt (maximum principal stress) and in the laminate (maximum stress in fiber direction, 11 ; and maximum out-of-plane stress, 33 ). The values of 33 in Table 4 were always compressive due to the nature of stress state induced on the plates.…”

Section: Stresses and Damage Indicatorsmentioning

confidence: 99%

“…These values were stated from similar applications in literature, as those proposed by Ekh and Scho¨n. 11,20 Loading path…”

Section: Numerical Model Model Descriptionmentioning

confidence: 99%

“…This fact has motivated the development of three dimensional models of the joint; 10 however, in some works, the influence of stacking sequence of the laminate was not accounted. 6,11 Aeronautical joints are manufactured under standard values of fastener torque. The level of torque applied to the bolt directly influences the stress fields in both the bolt and the composite plates.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Computational analysis of temperature effect in composite bolted joints for aeronautical applications

Santiuste

Barbero

Miguélez

2010

Journal of Reinforced Plastics and Composites

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This study focuses on the analysis of influence of temperature and bolt torque on aeronautical joint behavior. A single-lap joint, according to ASTM D5961, with a titanium bolt and composite plates was considered. A numerical model based on FEM was developed to evaluate the stress in both bolt and composite plates. Load-displacement curves, stress fields, and induced damage showed, significantly, the influence of temperature combined with torque level on the joint. It was found that in the plate, both maximum and minimum levels of torque considered produced damage above critical threshold. This fact should be accounted for, during the design process of the joint.

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Section: Stresses and Damage Indicatorsmentioning

confidence: 99%

“…These values were stated from similar applications in literature, as those proposed by Ekh and Scho¨n. 11,20 Loading path…”

Section: Numerical Model Model Descriptionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Computational analysis of temperature effect in composite bolted joints for aeronautical applications

Santiuste

Barbero

Miguélez

2010

Journal of Reinforced Plastics and Composites

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“…The eccentric load path in single shear lap joints adds the issue of lateral deflection (or secondary bending) of the joint, which generates a non uniform contact pressure between the fasteners and the hole edge. A stress singularity is also intro duced when the bolt is tilted in its hole as the surface contact changes into a line contact [19]. The analyses of the stress field in single lap bolted joints have shown that secondary bending produce non uniform stress distributions through the thickness of composite laminates in the vicinity of the bolt hole [5,20].…”

Section: Introductionmentioning

confidence: 99%

On the prediction of bolted single-lap composite joints

Olmedo

Santiuste

2012

Composite Structures

150

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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“…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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Effect of secondary bending on strength prediction of composite, single shear lap joints

Cited by 45 publications

References 33 publications

Computational analysis of temperature effect in composite bolted joints for aeronautical applications

Computational analysis of temperature effect in composite bolted joints for aeronautical applications

On the prediction of bolted single-lap composite joints

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

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