Bonded repair of a plate with inclined central crack under biaxial loading

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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“…In reality, composite patches with dropping-off plies [20,21] are proposed to reduce these high stresses so as to prevent debonding.…”

Section: Resultsmentioning

confidence: 99%

“…On the other hand, high effective stresses in the adhesive appear near the patch edge and may cause it to debond. To reduce the possibility of distortion damage, a taper angle at the patch edge should be introduced by dropping off patch plies[20,21]. The maximum effective stress in the adhesive occurs at the patch edge near the hole and the crack.…”

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confidence: 99%

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

1996

Self Cite

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“…The problem of edge debonding of patched structures has been extensively studied by Bottega (1995), Loia (1996, 1997), Bottega and Karlsson (1999), Karlsson and Bottega (1999a,b) and Carabetta (2007), for various issues and loading types. A thorough review and bibliography of the pertinent literature may be found in these works.…”

Section: Introductionmentioning

confidence: 99%

Effects of geometric nonlinearities on damage propagation in patched beam-plates subjected to pressure loading

Carabetta

Bottega

2008

Int J Fract

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The problem of edge debonding of patched beam-plates subjected to transverse pressure is examined using two related mathematical models; one which incorporates geometric nonlinearities and the other which neglects them. The models, developed in a prior study, present the energy release rates in self-consistent functional form and yield closed form analytical solutions for the specific problem of interest. Results of numerical simulations based on each model are presented in the form of debond growth paths and compared. The growth paths are subsequently presented with corresponding pre-growth load-deflection paths to further examine the differences resulting from each model. It is seen that significant discrepancies occur between the behaviors predicted by the two models, both with regard to the onset of damage propagation and with regard to the stability of the process, as well as with regard to the pre-growth behavior, demonstrating the critical influence of geometric nonlinearities on the phenomena of interest.

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“…A series of previously reported results have some limitation on the hypothesis that the structure is subjected uniaxial loading, but most of the structural components are subjected to biaxial loading. As the crack does not align with one of the principal directions, the mixed mode behavior will have a significant effect on the crack growth and fracture mechanics (Chue, et al, 1994).…”

Section: Introductionmentioning

confidence: 99%

Characterization of fracture behavior in repaired skin/stiffener structure with an inclined central crack

Chung

Yang

Heo

2002

KSME International Journal

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Finite element analysis for the stress intensity factor tSfF) at the skin/stiffener structure with inclined central crack repaired by composite stiffened panels is developed. A numerical investigation was conducted to characterize the fracture behavior and crack growth behavior at the inclined crack. In order to investigate the crack growth direction, maximum tangential stress (MTS) criterion are used. Also, this paper is to study the performance of the effective bonded composite patch repair of a plate containing an inclined central through-crack. The main objective of this research is the validation of the inclined crack patching design. In this paper, the reduction of stress intensity factors at the crack-tip and prediction of crack growth direction are determined to evaluate the effects of various non-dimensional design parameter including; composite patch thickness and stiffener distance. We report the results of finite element analysis on the stiffener locations and crack slant angles and discuss them in this paper. The research on cracked structure subjected to mixed mode loading is accomplished and concludes that more work using a different approaches is necessary. The authors hope the present study will aid those who are responsible for the repair of damaged aircraft structures and also provide general repair guidelines.

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Bonded repair of a plate with inclined central crack under biaxial loading

Cited by 58 publications

References 7 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

Effects of geometric nonlinearities on damage propagation in patched beam-plates subjected to pressure loading

Characterization of fracture behavior in repaired skin/stiffener structure with an inclined central crack

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