Bending of Bonded Composite Repairs for Aluminum Aircraft Structures: A Design Study

Clark, R. J.; Romilly, D.P.

doi:10.2514/1.30895

Cited by 15 publications

(11 citation statements)

References 33 publications

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“…Bending can be observed in adhesively bonded single-side composite patch repairs to metallic plates. Particularly, Clark et al [35] investigated bending of bonded composite repairs on cracked AA 2024-T3 plates.…”

Section: Introductionmentioning

confidence: 99%

On the static strength of aluminium and carbon fibre aircraft lap joint repairs

Pitta

Carles

Roure

et al. 2018

Composite Structures

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The behaviour of various aircraft lap joint repair configurations is investigated experimentally and numerically under static loading. The lap joints consist of aluminium alloy (AA) 2024-T3 substrates repaired with twin single-sided AA 2024-T3 or Carbon Fibre Reinforced Epoxy (CFRE) doublers. Pure riveted, pure bonded and hybrid (riveted and bonded) joints of metal-metal and metal-composite configurations are investigated. From experimental results, joints with adhesive bond showed nearly 5 times higher average strength than pure riveted joints, while hybrid joints performed better than riveted and bonded joints because of higher stiffness. On the other hand, hybrid metal-metal joint has 70% higher average strength compared to hybrid metal-composite joint. Rivet-shear has caused failure of riveted joints, and adhesive failure is observed in pure bonded joints. Hybrid joints with metal doublers have failed initially due to adhesive failure and later rivet shear. Interestingly, net-section failure is observed in composite doublers with breakage of doublers due to the presence of holes in the doublers. Experimental results are complemented with numerical analysis using commercial finite element code ABAQUS. Load-displacement curves obtained from the numerical results are in good agreement with experiments within a marginal error of 2%. In addition to load-displacement curves, a detailed stress analysis is performed numerically on metal-metal and metal-composite joints under riveted, bonded and hybrid configurations to study stress distribution on substrate and doublers. Numerical analysis showed hybrid and bonded joints have lower stresses in substrate and doublers compared to the riveted joints. Bonded joints have smoother load transfer due to the adhesive spread over a larger area. And finally, Stress Intensity Factors (SIFs) analysis is performed numerically for un-reinforced and reinforced metal substrate with a crack length of 1, 5 and 10 mm with metal and composite doublers under riveted and bonded configuration. For crack of 10 mm, 35% reduction in SIFs is observed for reinforced substrate with bonded metal or composite doublers compared to the un-reinforced cracked substrate.

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Section: Introductionmentioning

confidence: 99%

On the static strength of aluminium and carbon fibre aircraft lap joint repairs

Pitta

Carles

Roure

et al. 2018

Composite Structures

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“…The effect of bending fatigue loading has been investigated by a few authors. Clark and Romilly [42] presented an experimental and FEA study of a bonded composite repair applied to a metallic aircraft structure. They performed fatigue testing of 2024-T3 Al plates repaired with boron/epoxy composite patches.…”

Section: Effect Of Loadingmentioning

confidence: 99%

Fatigue in Adhesively Bonded Joints: A Review

Wahab

2012

ISRN Materials Science

116

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This paper presents a literature review on fatigue in adhesively bonded joints and covers articles published in the Web of Science from 1975 until 2011. About 222 cited articles are presented and reviewed. The paper is divided into several related topics such as fatigue strength and lifetime analysis, fatigue crack initiation, fatigue crack propagation, fatigue durability, variable fatigue amplitude, impact fatigue, thermal fatigue, torsional fatigue, fatigue in hybrid adhesive joints, and nano-adhesives. The paper is concluded by highlighting the topics that drive future research.

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“…The majority of the studies are dedicated to repairs of metallic structures with composite patches [1][2][3]. Baker [1] studied repairs based on adhesively bonded fibrecomposite patches or reinforcements on defective or degraded metallic aircraft components.…”

Section: Introductionmentioning

confidence: 99%

“…The experimental strain data, together with a specific fatigue curve experimentally defined provided the input of a finite element model of the repaired structure and resulted in the expected fatigue life of the repair metal-composite. Clark and Romilly [3] performed experimental and finite element studies of a bonded composite repair on metallic aircraft structure. They concluded that bending and composite failure modes play an important role on the fatigue lifetime.…”

Section: Introductionmentioning

confidence: 99%