Effects of external patch configuration on repaired composite laminates subjected to multi-impacts

Coelho, Sara R. M.; Reis, P.N.B.; Ferreira, J.A.M.; Pereira, A.M.

doi:10.1016/j.compstruct.2017.02.069

Cited by 60 publications

(40 citation statements)

References 68 publications

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“…On the other hand, external patch repair is relatively simple and faster, hence it is widely used in aircraft to keep an airplane in serviceable condition. Considerable experimental and numerical studies have been conducted to optimize the geometrical parameters of external patch repair and scarf repair joints for the better performance of the composite repair [10][11][12][13][14][15][16][17]. However, designing an optimum scarf and patch repair of a composite structures is complex due to an unpredicted environmental condition during service period.…”

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confidence: 99%

Bonded repair of composite structures in aerospace application: a review on environmental issues

2018

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IntroductionOutstanding properties of fiber reinforced polymer composite materials, lead to a wide application in all the sectors such as aerospace, automotive, marine, sports industries and even in the civil infrastructures, etc. Since the last decades, an enormous use of composite materials in the aerospace sector has caused an increasing need for repair technology of damaged component rather than replacement with a new component [1][2][3][4]. Composite structures in service experience damage that comes from the accidental impact and mechanical or environmental condition [5,6]. The main environmental threats are related to the effect of temperature and moisture absorption, which can affect the strength of composite structures and reduce their service life [4,7,8]. The temperature and moisture levels could vary throughout the day (see Fig. 1), from take off to the landing or vice versa, during seasonal change or geographical difference [9]. This cyclic temperature and moisture could even further deteriorate the structures and then lead to premature failure of the structure. AbstractOver the last two decades, the repair of existing engineering structures using fiber reinforced polymer composites has attracted a great attention by aerospace industry, as it is more economical than replacing new. With an increased use of composite material in aerospace field, it is thus essential to restore the structural integrity by repair of damaged part. Concerns regarding the long term durability of composite repair bonded joints have been a major obstacle for critical component of aerospace structures. This paper reviews the current research on the environmental durability of adhesive bonded repair of composite structures to focus on the durability concerns and suggestion on the research needed in this area. The most important environmental factors (moisture and temperature) are reviewed thoroughly and also combined environmental effect. Finite element methods used to predict the environmental influence on the composite bonded joints are briefly reviewed. Finally, the paper concludes with key findings, opportunities and future research topics in order to develop cost effective, better quality and reliable composite repair bonded joints.

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confidence: 99%

Bonded repair of composite structures in aerospace application: a review on environmental issues

2018

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“…First, a single-sided patch was more effective when applied to the opposite side rather than the same side of the plate as the stiffening members. Coelho et al (Coelho et al, 2017) studied the impact performance of repaired by overlap composite patches. They used single and double-patch specimens to experiment.…”

Section: Figure 1 Different Repair Technique For Laminated and Sandwmentioning

confidence: 99%

“…The determining other issues are that choosing the suitable patch for the damaged materials, measuring the strength of the damaged materials after applying the patch. The 49 researches about composite materials increase and they are used by basis and auxiliary material in the most of the recent applications (Çalışkan et al, 2017, Maamar et al, 2015, Pandey and Kumar, 2010, Kwon and Hall, 2015, Coelho et al, 2017, Deng et al, 2017. Impact response of material may depend on its application area and aim.…”

Section: Introductionmentioning

confidence: 99%

Kompozit Yamalar ile Tamir Edilen Hasarlı Kompozit Plakaların Düşük Hızlı Darbe Davranışı

Çalışkan¹,

Ekici²,

Apalak³

2019

Mehmet Akif Ersoy Üniversitesi Uygulamalı Bilimler Dergisi

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Adhesive bonding technique is used in many engineering applications. Repairing with fiber composite patches using adhesive bonding technique are widely used for repairing cracks or other defects. Patch application to damaged materials with adhesive bonding is used to extend the service life of the material. In this study, patches were bonded damaged fiber-reinforced laminated composite plates and the dynamic load resistance was investigated numerically.Damaged composite plates and fiber reinforced composite patches are bonded with adhesive.Non-linear finite element analyses were performed in the ABAQUS finite element software.A cohesive zone model based on fracture mechanics was used as the adhesive material model.Low velocity impact behavior of damaged plates repaired by composite patches was also investigated for different patch material such as aluminum and fiber reinforced composite. Impact analyses performed on different impact energy with constant impactor weight were investigated in terms of contact force variations, kinetic energy variations and impact damage.Damaged plates without patch were perforated and damaged. Composite patches absorb impact energy and prevent the perforation. Yapıştırıcı ile birleştirme tekniği birçok mühendislik uygulamalarında kullanılmaktadır. Yapıştırma tekniği ile kullanılan fiber takviyeli kompozit yamalar ile tamir, çatlakların ve diğer hasarların tamirinde geniş çapta kullanılmaktadır. Yapıştırma tekniği ile hasarlı malzemelere yapıştırılan yama uygulamaları, malzemelerin kullanım ömürlerini uzatmak için kullanılmaktadır. Bu çalışmada, yamalar hasara uğramış fiber takviyeli kompozit plakalara yapıştırılmış ve dinamik yük dayanım kabiliyeti nümerik olarak araştırılmıştır. Yamalar ve hasarlı kompozit plakalar yapıştırıcı kullanılarak birleştirilmiştir. Lineer olmayan sonlu elemanlar analizleri ABAQUS sonlu elemanlar yazılımı kullanılarak yapılmıştır. Kırılma mekaniği temelli kohezif bölge modeli yapıştırıcı malzemesinin modellenmesinde kullanılmıştır. Yamalar kullanılarak tamir edilen hasarlı plakaların düşük hızlı darbe davranışı kompozit ve alüminyum yama malzemesi kullanılarak farklı yama malzemeleri içinde araştırılmıştır. Darbe analizleri, sabit kütleli vurucu ile farklı darbe enerjilerinde yapılırken temas kuvveti değişimi, kinetik enerji değişimi ve darbe hasarı açısından da araştırılmıştır. Yamasız hasarlı plaka delinerek hasara uğramıştır. Kompozit yamalar darbe enerjisini sönümlemekte ve delinmeyi önlemekte başarılı bir davranış sergilemiştir. Anahtar kelimeler: Kompozit Yama, Düşük Hızlı Darbe, Yapıştırıcı, Lineer Olmayan Sonlu Elemanlar Metodu.

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“…Traditionally it is used the bonded repairs, where the adhesive layer transfer some load from one part of the component to other one reducing, in this case, the stresses in the repaired component. Mainly two types of patch configurations are available: the scarf patches and the overlap patch [1][2][3][4]. However, according to Soutis et al [2], the external patch technique is simpler to apply and is less critical in nature than a scarf method.…”

Section: Introductionmentioning

confidence: 99%

Repair Delaminations in Carbon/epoxy Laminates

et al. 2019

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Delaminations are the most typical damage in composite laminates, and the industrial community is continually searching new techniques to combine efficiency with cost benefits. Therefore, this work intends to analyse the application of screws on repair of composite laminates containing delaminations. It was found that this technique is beneficial for delaminations with lengths higher than 15 mm. For example, considering delaminations with 20 mm, the compressive load increases around 46.4% relatively to the delaminated samples. However, for small lengths, this technique is not viable due to the stress concentration induced by the hole.

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Effects of external patch configuration on repaired composite laminates subjected to multi-impacts

Cited by 60 publications

References 68 publications

Bonded repair of composite structures in aerospace application: a review on environmental issues

Bonded repair of composite structures in aerospace application: a review on environmental issues

Kompozit Yamalar ile Tamir Edilen Hasarlı Kompozit Plakaların Düşük Hızlı Darbe Davranışı

Repair Delaminations in Carbon/epoxy Laminates

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