Effects of composite adherend properties on stresses in double lap bonded joints

Mokhtari, Mohamed; Madani, K.; Belhouari, M.; Touzain, S.; Feaugas, X.; Ratwani, M.

doi:10.1016/j.matdes.2012.08.001

Cited by 38 publications

(15 citation statements)

References 28 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Adhesive bonding method is already a well matured and developed process and was reviewed by many authors [18][19][20][21][22]. Many researchers [23][24][25][26][27][28][29][30] studied the performance of adhesively bonded joints under the influence of different geometry and material parameters. Adhesive bonded repair in composite components are well established and developed in the aeronautical industry [31][32][33].…”

mentioning

confidence: 99%

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

2018

View full text Add to dashboard Cite

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.

show abstract

mentioning

confidence: 99%

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

2018

View full text Add to dashboard Cite

show abstract

“…The same thing in the compressive behavior but we restraint vertically all length except overlap region the both of the edge in order to favorite the separation, and the tensile replaced by the compressive displace. The choice of our geometric model in three dimensions, in single and double overlap with composite plates is standardized Mokhtari [27,28]. See also the works of Benchiha [29] who carried out a study on the influence of defects and the work of Bezzerrouki [30], who has carried out several studies in this line of research.…”

Section: Discussionmentioning

confidence: 99%

Using a cohesive zone modeling to predict the compressive and tensile behavior on the failure load of single lap bonded joint

Benamar

Mokhtari

Madani

et al. 2019

Frattura Ed Integrità Strutturale

View full text Add to dashboard Cite

The aim of this work is to analyze the failure behavior of a simple lap joint of type metal / metal consisting of 2024-T3 Aluminum plate bonded with an Araldite adhesive using the finite element method to predict damage of the metal in tensile and compressive load under the effect of geometric parameters such as the length of the overlap and the geometric shape of the two plates according to the overlap length. The numerical analysis is performed by the ABAQUS calculation code. The adhesive was modeled by an element of the CZM cohesive zone. the adhesive will be submitted in mixed mode given the non-linearity of the two applied load. the calculation of the failure load will be determined according to the different parameters mentioned above. It is well demonstrated that the type of loading and the parameters taken into consideration condition the strength of the structure. The effect of these different parameters on the strength of the adhesive joint is presented as results by failure load curves.

show abstract

“…In our analysis, the stiffness is not only due to the composite (Mokhtari et al, 2013;Campilho et al, 2005), but it is the composite/adhesive/composite stiffness. Figure 7 shows the composite/adhesive/composite stiffness during loading for each laminate.…”

Section: Effect Of Stacking Sequence and Layers Thickness Of The Lamimentioning

confidence: 99%

Effects of the composite stacking sequence on the failure load of the single lap bonded joint

Mokhtari

Madani²,

Benzaama

et al. 2017

jtam

View full text Add to dashboard Cite

Composite materials are widely used in aircraft structures, their relative rigidity/weight confers their advantage over metal structures, and the stacking sequence plays an important role for their use. The objective of this work is to analyze by the finite element method the mechanical behavior of a single lap joint of composite/composite type under a tensile load. In order to see the effects on the failure load, two basic parameters are taken into consideration; the stacking sequence of composite and thickness of each layer constituting the composite. Calculation of the failure load is made numerically with the ABAQUS code using the developed technique of VCCT (Virtual Crack Closure Technique) based on fracture mechanics. Finally, the influence of the bonding defect on the failure load is analyzed. The results clearly show the importance of optimizing fiber orientation and hence the stacking sequence for proper use of composite in bonded assemblies.

show abstract

Effects of composite adherend properties on stresses in double lap bonded joints

Cited by 38 publications

References 28 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

Using a cohesive zone modeling to predict the compressive and tensile behavior on the failure load of single lap bonded joint

Effects of the composite stacking sequence on the failure load of the single lap bonded joint

Contact Info

Product

Resources

About