Stress analysis and strength prediction of mechanically fastened joints in FRP: a review

Camanho, P.P.; Matthews, F.L.

doi:10.1016/s1359-835x(97)00004-3

Cited by 314 publications

(125 citation statements)

References 68 publications

Supporting

Mentioning

121

Contrasting

Unclassified

Order By: Relevance

“…Effects such as bolt clamp up and secondary bending are best accounted for by 3D models, while the bearing mode of failure is a 3D phenomenon, involving through thickness cracks and delaminations [2].…”

Section: Introductionmentioning

confidence: 99%

On the prediction of bolted single-lap composite joints

Olmedo

Santiuste

2012

Composite Structures

156

103

View full text Add to dashboard Cite

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.

show abstract

Section: Introductionmentioning

confidence: 99%

On the prediction of bolted single-lap composite joints

Olmedo

Santiuste

2012

Composite Structures

156

103

View full text Add to dashboard Cite

show abstract

“…Hole vicinities are the areas of high stress concentrations and they determine load capability of the whole structure. Therefore, mechanical joints of composite parts require a special focus during both a designing [2,3] and a manufacturing process [4]. The aim of the paper is analysis of potential local material weakness/deterioration caused by a drilling process and its influence on the global response of a mechanical joint.…”

Section: Object Of Analysismentioning

confidence: 99%

Gradient material model in analysis of mechanical joints of CFRP laminate

Puchała¹,

Szymczyk²,

Jachimowicz³

et al. 2018

AIP Conference Proceedings

View full text Add to dashboard Cite

“…A large number of FE-studies of bolted joints with composite plates exist in the literature [104]. 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.…”

Section: Modelling Of Quasi-static Failurementioning

confidence: 99%

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

Kapidžić¹

2015

View full text Add to dashboard Cite

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

show abstract

Stress analysis and strength prediction of mechanically fastened joints in FRP: a review

Cited by 314 publications

References 68 publications

On the prediction of bolted single-lap composite joints

On the prediction of bolted single-lap composite joints

Gradient material model in analysis of mechanical joints of CFRP laminate

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

Contact Info

Product

Resources

About