The effects of laminated composite patch with different stacking sequences on bonded repair

Chue, Ching‐Hwei; Liu, Thomas Jin-Chee

doi:10.1016/0961-9526(95)90715-n

Cited by 24 publications

(15 citation statements)

References 17 publications

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“…This numerical result also coincides with that of Ref. [18]. The data in Tables III and VII show that In addition, Table VIII shows the maximum absolute values of von Mises effective stresses o e in the adhesive and the fiber stresses o-f in the patch.…”

Section: Case A: the Effects Of Patch Sizesupporting

confidence: 76%

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The effects of size and stacking sequence of composite laminated patch on bonded repair for cracked hole

1996

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The performance of a bonded repair for cracked holes has been studied using the three dimensional finite element method, linear elastic fracture mechanics and strain energy density theory. Increasing the composite patch size reduces the strain energy level at the crack tip; increasing the patch length normal to the crack is a better choice. The stacking sequences of the laminated patch have little influence on the strain energy distribution in the vicinity of the crack. To repair the cracked holes of aircraft components subjected to variable direction loading during flight, the orientations of the patch ply, 90 ~ and 4-45 ~ with respect to the crack direction, are the optimum selection in bonded repairs.

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Section: Case A: the Effects Of Patch Sizesupporting

confidence: 76%

“…This result matches with ref. [18] and simplifies the procedure of selecting optimum ply orientations. According to the proposal in [19], a general design guideline about patching repairs is suggested that the ply orientation should be selected to have the max- 12 18 L (mm) Figure 3.…”

Section: Case A: the Effects Of Patch Sizementioning

confidence: 99%

The effects of size and stacking sequence of composite laminated patch on bonded repair for cracked hole

1996

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“…(2) By increasing the crack length ratio, the strength of specimens decreases, no matter they are repaired or not. (3) No matter what the type of the crack is, the strength of the repaired structures depends on the type of patch lay-up. The more the metal layer of the patch structure is close to the repaired surface, the more the energy absorbs in the structure.…”

Section: Discussionmentioning

confidence: 99%

“…The positive effect of using composite patches to improve the mechanical behavior of cracked components was first studied by the Aeronautical and Maritime Research Laboratory [2]. Chue et al [3] discussed the effect of laminated composite patch with different stacking sequences on repairing an inclined central cracked plate under biaxial loads. They showed that the use of different stacking sequences for the patch does not affect the energy distribution near the crack tip significantly.…”

Section: Introductionmentioning

confidence: 99%

A Study on the Charpy Impact Response of the Cracked Aluminum Plates Repaired with FML Composite Patches

Ghasemi

Vanani

Anaraki

2016

J Fail. Anal. and Preven.

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Fiber metal laminates (FMLs) are widely used in aerospace industries nowadays. Reparation of the cracks in these advanced materials was first done by some aeronautical laboratories in the early 1970s. In this study, experimental investigations were done on the effects of repairing the edge-cracked aluminum plates using the FML patches. The repairing processes were conducted to characterize the response of the repaired structures to the Charpy impact tests. The composite patches were made of one aluminum layer and two woven glass-epoxy composite layers. Three different crack lengths, crack angles, and patch lay-ups were examined. It was indicated that for the lengthen cracks, the effect of increasing the crack angle on energy absorption in the structure was more. When the ratio of crack length to the specimen width, i.e., a/w, is 0.5, the energy absorption per unit area of the specimens having different crack angles but the same patch lay-ups was so different. It was also observed that the percentage of the absorbed energy of 45°cracked angle specimens was about 25% higher than the 0°ones. Also it was observed that the lay-up of the patches and the place where the metal layer was embedded in the FML patches had an important effect on the impact response of the tested specimens. The more the metal layer of the patches is far from the interfacial surface of the aluminum plate and the FML patches, the less the energy absorbs in the structure.

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“…In addition, ply orientations also play an important role in altering the stress distribution of composite laminates. In bonded repair of cracks in aircraft components, laminated composite patch with ply orientations of 0¡, +45¡, -45¡ and 90¡ have been favourable with the +45¡, -45¡ and 90¡ orientation to crack direction being identified as the optimal design where variable flight loadings are concern (Chue and Liu, 1995;Baker and Jones, 1988). Thus, it is also of importance that the fiber recipe be considered in the design of such structures, especially for flywheels spun at high operating speed.…”

Section: Introductionmentioning

confidence: 99%

Interlaminar stress analysis for carbon/epoxy composite space rotors

Lian

Varatharajoo

Suhadis

2011

The International Journal of Multiphysics

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The effects of laminated composite patch with different stacking sequences on bonded repair

Cited by 24 publications

References 17 publications

The effects of size and stacking sequence of composite laminated patch on bonded repair for cracked hole

The effects of size and stacking sequence of composite laminated patch on bonded repair for cracked hole

A Study on the Charpy Impact Response of the Cracked Aluminum Plates Repaired with FML Composite Patches

Interlaminar stress analysis for carbon/epoxy composite space rotors

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