Stress and failure analysis of mechanically fastened joints in composite laminates

Dano, Marie‐Laure; Gendron, Guy; Picard, André

doi:10.1016/s0263-8223(00)00119-7

Cited by 148 publications

(78 citation statements)

References 22 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…The large number of variables within any joint design makes it difficult and expensive to test even a small range of joints comprehensively. Therefore many attempts have been made to understand and predict the failure of composite joints [8][9][10][11][12][13][14][15][16][17][18][19][20][21][22][23][24][25] using numerical and analytical methods to reduce the experimental effort required. Most successful joint modelling has been conducted with slow design tools, i.e.…”

mentioning

confidence: 99%

Experimental Investigation of Dynamically Loaded Bolted Joints in Carbon Fibre Composite Structures

Pearce

Johnson

Thomson³

et al. 2009

Appl Compos Mater

View full text Add to dashboard Cite

This paper reports on recent experimental work to investigate the response of bolted carbon fibre composite joints and structures when subjected to constant dynamic loading rates between 0.1 m/s and 10 m/s. Single fastener joints were tested in both the bearing (shear) and pull-through (normal) loading directions. It was found that the joints exhibited only minor loading rate dependence when loaded in the pull-through direction but there was a significant change in failure mode when the joints were loaded in bearing at or above 1 m/s. Below 1 m/s loading rate the failure mode consisted of initial bolt bearing followed by bolt failure. At a loading rate of 1 m/s and above the bolt failed in a 'tearing' mode that absorbed significantly more energy than the low rate tests. A simple composite structure was created to investigate the effect of loading rate on a more complex joint arrangement. The structure was loaded in two different modes and at constant dynamic loading rates between 0.1 m/s and 10 m/s. For the structure investigated and the loading modes considered, only minor loading rate effects were observed, even when the dominant contribution to joint loads came from bearing. It was observed that the load realignment present in the structural tests allowed the joints to fail in a mode that was not bearing dominant, and hence the loading rate sensitivity was not expressed.

show abstract

mentioning

confidence: 99%

Experimental Investigation of Dynamically Loaded Bolted Joints in Carbon Fibre Composite Structures

Pearce

Johnson

Thomson³

et al. 2009

Appl Compos Mater

View full text Add to dashboard Cite

show abstract

“…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

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

“…Stresses and strains are computed at each incremental load step and evaluated by the failure criteria to determine the occurrence of failure and the mode of failure. The detailed procedures are reported in reference [9]. The constitutive behavior of the layer, as de- 4), is accessible at every integration point in each element with UMAT.…”

Section: Mpamentioning

confidence: 99%

Simulation and experimental studies of the repaired composite laminate

Jiang

Zhu

2006

Mat.-wiss. u. Werkstofftech.

View full text Add to dashboard Cite

Firstly the compress experiment is undertaken to investigate the efficiency of repaired panels in this paper, and then modeling of the mechanical behavior of the repaired composite panel under compressive static load is conducted by using of the finite element method. The effect of geometric non-linearity on the stress-strain response is considered in the numeric analysis. Fatherly, the user material subroutine (UMAT) is integrated with the ABAQUS package with the geometric non-linearity effect for studying the damage initiation and its progression in the composite structure, and quadrilateral, linear, thick shell elements (S8R) are adopted. Finally, the predicted strain distribution, damage evolution and strength of the laminate are compared with the test results.

show abstract

Stress and failure analysis of mechanically fastened joints in composite laminates

Cited by 148 publications

References 22 publications

Experimental Investigation of Dynamically Loaded Bolted Joints in Carbon Fibre Composite Structures

Experimental Investigation of Dynamically Loaded Bolted Joints in Carbon Fibre Composite Structures

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

Simulation and experimental studies of the repaired composite laminate

Contact Info

Product

Resources

About