Selection of patch and adhesive materials for helicopter battle damage repair applications

Wang, John; Zhou, Zhong Qing; Vodicka, Roger; Chiu, Wing Kong

doi:10.1016/j.compstruct.2009.04.042

Cited by 22 publications

(12 citation statements)

References 6 publications

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“…Carbon-fibre reinforced plastic (CFRP) components are being more and more used in structures demanding a high performance because of their superior characteristics (such as high strength, high stiffness, long fatigue life and low density) [1]. In spite of these advantages, CFRP materials usually show a high sensitivity to temperature, moisture and accidental impacts.…”

Section: Introductionmentioning

confidence: 99%

Numerical evaluation of three-dimensional scarf repairs in carbon-epoxy structures

Pinto¹,

Campilho

Moura

et al. 2010

International Journal of Adhesion and Adhesives

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The widespread employment of carbon-epoxy laminates in high responsibility and severely loaded applications introduces an issue regarding their handling after damage. Repair of these structures should be evaluated, instead of their disposal, for cost saving and ecological purposes. Under this perspective, the availability of efficient repair methods is essential to restore the strength of the structure. The development and validation of accurate predictive tools for the repairs behaviour are also extremely important, allowing the reduction of costs and time associated to extensive test programmes. Comparing with strap repairs, scarf repairs have the advantages of a higher efficiency and the absence of aerodynamic disturbance. This work reports on a numerical study of the tensile behaviour of three-dimensional scarf repairs in carbon-epoxy structures, using a ductile adhesive (Araldite s 2015). The finite elements analysis was performed in ABAQUS s and Cohesive Zone Modelling was used for the simulation of damage onset and growth in the adhesive layer. Trapezoidal cohesive laws in each pure mode were used to account for the ductility of the specific adhesive mentioned. A parametric study was performed on the repair width and scarf angle. The use of over-laminating plies covering the repaired region at the outer or both repair surfaces was also tested as an attempt to increase the repairs efficiency. The obtained results allowed the proposal of design principles for repairing composite structures.

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Section: Introductionmentioning

confidence: 99%

Numerical evaluation of three-dimensional scarf repairs in carbon-epoxy structures

Pinto¹,

Campilho

Moura

et al. 2010

International Journal of Adhesion and Adhesives

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“…In contrast, all repaired specimens containing fiber reinforcement exhibit a better response to local bending load. 2 The results indicate that reinforcing the polymer matrix with fibers can hinder the crack propagation under out-of-plane loading. Damaged glass/epoxy specimens repaired using chopped short fibers and exposed to a post-cure temperature of 50ºC showed the most favorable indentation behavior.…”

Section: Discussionmentioning

confidence: 95%

“…Physical damage in laminate composites degrades their mechanical properties and hence reduce their service life. Hence, strategies are needed to recover the mechanical strength of structural components damaged from accidental physical events, such as bird strikes, external environmental factors e.g., lightning strikes, temperature and moisture, fall of hailstones, or tools dropping during maintenance [2][3]. In particular, the increasing use of composite laminates in high performance structures, coupled with possible cost minimization, suggest to attribute considerable importance to their repair, also because replacement of complexly integrated structures presenting only minor damage may prove unnecessary: repair can be a way of economically enhancing service life of structural components [4][5].…”

Section: Introductionmentioning

confidence: 99%

Effect of post-cure temperature and different reinforcements in adhesive bonded repair for damaged glass/epoxy composites under multiple quasi-static indentation loading

Andrew

Arumugam

Santulli

2016

Composite Structures

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“…Similarly, Temiz et al [12] tried to increase the strength of the single lap joint by beveling the edges of the joint. Campilho et al [13] studied the tensile behavior of the 3D single and double strap joints made out of carbon-epoxy composites experimentally Wang et al [15] performed studies for the selection of the composite material so as to repair of the vehicles, such as damaged planes, helicopter etc, rapidly. Meanwhile, stress behavior of the CFRP laminates which were bonded as double strap and subjected to tensile loading was studied by Liu and Wang [16].…”

Section: Introductionmentioning

confidence: 99%

Stress analysis of adhesively bonded double strap joints with or without intermediate part subjected to tensile loading

Çitil

Ayaz

Temiz

2015

The Journal of Adhesion

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Accidents in the industry, especially in the field of aerospace, are quite common.Damages like tears cracks and holes occur especially when small sand particles present in the airfield collide with the body and wings of an airplane during takeoff and landing. This torn, cracked or pierced region should be repaired gently. Damaged parts are frequently small regions which repair is more suitable than complete replacement as workmanship; cost and time are an important concept in today's world. A gap occurs between the patches if double-bonded patches are used in the repair of the damaged parts. In this study, the region between patches in a joint with and without intermediate parts was modeled and its effect on strength was examined numerically and experimentally. The effect of patch thickness, overlap length, adherent thickness and gap length, on the strength of the joints with and without intermediate part was compared. The results show that the intermediate part does not have any influence on the strength of the lap joint such that double strap joints without intermediate part have higher failure Downloaded by [Cambridge University Library] at 07:06 14 August 2015 2load. Additionally, it is seen that the failure load decreased with increasing patch thickness and increased with the thickness of the adherent.

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Selection of patch and adhesive materials for helicopter battle damage repair applications

Cited by 22 publications

References 6 publications

Numerical evaluation of three-dimensional scarf repairs in carbon-epoxy structures

Numerical evaluation of three-dimensional scarf repairs in carbon-epoxy structures

Effect of post-cure temperature and different reinforcements in adhesive bonded repair for damaged glass/epoxy composites under multiple quasi-static indentation loading

Stress analysis of adhesively bonded double strap joints with or without intermediate part subjected to tensile loading

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