Fatigue of multiple-row bolted joints in carbon/epoxy laminates: ranking of factors affecting strength and fatigue life

Persson, Erik; Eriksson, Ingvar

doi:10.1016/s0142-1123(98)00081-4

Cited by 26 publications

(11 citation statements)

References 11 publications

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“…The joint strength was reduced by 3.6% at 82°C. A study by Persson and Eriksson [15] involved testing of multiple-row joints in the CFRP material HTA/6376 at 70°C. The temperature was found to have no effect on the strength.…”

Section: Introductionmentioning

confidence: 99%

Quasi-static bearing failure of CFRP composite in biaxially loaded bolted joints

Kapidžić

Ansell²,

Schön

et al. 2015

Composite Structures

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Section: Introductionmentioning

confidence: 99%

Quasi-static bearing failure of CFRP composite in biaxially loaded bolted joints

Kapidžić

Ansell²,

Schön

et al. 2015

Composite Structures

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“…There are many other factors that influence the failure behaviour and the strength of shear loaded bolted joints [43] and many of them have been studied in the literature using both experimental and analytical methods. 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.…”

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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“…Persson and Eriksson [1999] conducted an experimental investigation with the objective of ranking the factors that most significantly affect strength and fatigue life in multi-row, carbon-epoxy bolted joints, using a linear regression analysis. For static loading, it was found that the most influential factors were the bolt diameter to laminate thickness ratio (dit), the bolt preload, and the bolt-head type.…”

Section: Composite Bolted Joints Subjected To Fatigue Loadingmentioning

confidence: 99%

Testing and Analysis of Hybrid Composite/Metal Connections and Hull Section for the MACH Project

Kabche¹,

Caccese²,

Berube³

2006

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This report summarizes the development, testing and analysis of hybrid composite/metal connections and hybrid structural systems under the Modular Advanced Composite Hullform (MACH) project. The MACH project, funded by the Office of Naval Research, is part of a joint effort between the University of Maine, Navatek of Honolulu, HI, and Applied Thermal Sciences (ATS) of Sanford, Maine, and is performed in conjunction with the Naval Surface Warfare Center at Carderock, MD (NSWCCD). The primary motivation for the work summarized herein is to provide alternatives to conventional hull construction techniques and conventional hull forms by using modular hybrid construction methods. Included is a description of tests performed on sub-scale hybrid bolted connections, where the objective was to develop watertight connections for removable panels. An experimental study was conducted to quantify the performance of numerous hybrid joints with various geometries, loaded in flexure. The test results showed that for resisting bending loads, joints with doubler plates can be made stronger and rotationally stiffer than standard bolted joints, while also mitigating opening of the joint, thereby improving the ability to seal the connection for watertight integrity.The results of this study were used to select a connection geometry, which was incorporated into the hydrostatic testing of a full-scale four-panel assembly. Testing of the assembly is described in this report and shows that a linear response of the system was observed up to its design pressure load of 82.74 kPa. Damage initiated as stiffener delamination at 1.4 times the design load. After failure of several stiffeners, the hybrid assembly withstood up to 3 times its design load without leakage. Hence, the response of the hybrid joint employed was deemed successful.Numerical analysis of the connections and assembly are also presented. Simplified shell finite element models were developed at both local and global levels. These models were for estimation of the joint stiffness and good correlation with the test results was observed. Strength of the system was predicted using detailed plane strain contact models to capture the three-dimensional effects of the connection. ii ACKNOWLEDGMENTSThe authors gratefully acknowledge funding for this project through the Office of Naval

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Fatigue of multiple-row bolted joints in carbon/epoxy laminates: ranking of factors affecting strength and fatigue life

Cited by 26 publications

References 11 publications

Quasi-static bearing failure of CFRP composite in biaxially loaded bolted joints

Quasi-static bearing failure of CFRP composite in biaxially loaded bolted joints

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

Testing and Analysis of Hybrid Composite/Metal Connections and Hull Section for the MACH Project

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