The development of fatigue damage around fastener holes in thick graphite/epoxy composite laminates

Saunders, D. S.; Galea, Steve C; Deirmendjian, G.K.

doi:10.1016/0010-4361(93)90041-6

Cited by 81 publications

(34 citation statements)

References 6 publications

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“…Finally, fibre kinking takes place at the hole edge and spreads thereafter in the radial direction, whereupon structural failure occurs. Similarly, studies of bearing failure in cyclic loading [36][37][38][39][40][41][42], reveal matrix shear cracking and delamination and in some cases bolt fatigue failure. Significant increase in compliance, accompanied by hole elongation is observed during the cycling.…”

Section: Bolted Jointsmentioning

confidence: 97%

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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Section: Bolted Jointsmentioning

confidence: 97%

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

Kapidžić¹

2015

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“…Dioctylphthalate (DOP) was a commercial grade, supplied by Rubo-Synth impex Pvt. Ltd. Magnesium oxide was also a commercial grade calcined light magnesia with a specific gravity of 3.6 g/cm 3 , supplied by Central Drug House Pvt. Ltd., Mumbai.…”

Section: Composite Preparationmentioning

confidence: 99%

“…Viton A401C, a fluoroelastomer containing bisphenol curatives with specific gravity of 1.82 g/cm 3 and Mooney viscosity 42 at 120℃ was obtained from DuPont Dow Elastomers. Dioctylphthalate (DOP) was a commercial grade, supplied by Rubo-Synth impex Pvt.…”

Section: Composite Preparationmentioning

confidence: 99%

“…The samples were heated from room temperature to 800℃ at a heating rate of 20℃/min and a nitrogen gas flow rate of 40-50 cm 3 /min. The sample weight varied from 10-15 mg.…”

Section: Composite Characterizationmentioning

confidence: 99%

“…There are four factors affecting the process of combustion, which are oxygen, heat, flammable materials and thermal degradation [2]. Brominated flame retardants, which stop the thermal degradation of composites by reacting with polymers, are the most effective flame retardants in the market that are adopted for most engineering polymers [3]. However, halogenated flame retardants release toxic gases when they are subjected to high temperatures.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Effect of Aluminium Hydroxide on Thermal, Dynamic Mechanical and Dielectric Properties of Hexafluoropropylene-vinylidinefluoride Elastomeric Composites

Nair¹,

Vijayan²,

Ayswarya³

et al. 2017

JAN

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Abstract. Aluminium hydroxide (ATH) particles were incorporated at different loadings into fluorocarbon rubber (FKM), to study the effect of filler loading on the cure characteristics, mechanical properties, dynamic mechanical properties and thermal stability. The mechanical properties of FKM/ATH composites were better than medium thermal black filled vulcanizates. The storage modulus (E') of the composites was found to increase due to the enhancement in stiffness. The viscoelastic properties revealed that there is a strong interaction between the polymer and the filler. The dielectric permittivity, AC conductivity and absorption coefficient of the highly ATH loaded systems are much greater than the unfilled and lower systems.

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References

2017

Handbook of Structural Life Assessment

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The development of fatigue damage around fastener holes in thick graphite/epoxy composite laminates

Cited by 81 publications

References 6 publications

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

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

Effect of Aluminium Hydroxide on Thermal, Dynamic Mechanical and Dielectric Properties of Hexafluoropropylene-vinylidinefluoride Elastomeric Composites

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