Boundary element analysis of cracked panels repaired by mechanically fastened composite patches

Widagdo, Djarot; Aliabadi, M.H.

doi:10.1016/s0955-7997(01)00026-1

Cited by 8 publications

(9 citation statements)

References 7 publications

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“…A different behaviour between BEM and FEM is noticed; for long joints the BEM predicts a homogeneous F x distribution along the same row, while in FEM it goes from a lower F x at the edge rivets for short joints to higher values for long joints. Widagdo and Aliabadi 11 performed a 2D BEM study, and the behaviour is similar to the plate BEM presented here. Although the trend is different, the difference in values is small.…”

Section: Numerical Examplessupporting

confidence: 60%

“…Here a BEM formulation for riveted plate structures is presented, thus the bending effects are considered. The approach followed is similar to the one proposed by Salgado and Aliabadi 3 and Widagdoo and Aliabadi 11 for 2D, and extended to shear-deformable plates. No friction between plates is considered, and the rivets are modelled as attached points; although this affects local results, it is considered of minor influence when large structures are studied.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Boundary element analysis of riveted aircraft panels

Pisa

Aliabadi²

2012

The Journal of Strain Analysis for Engineering Design

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In this paper the boundary element method is applied to riveted aircraft structures. There are several ways of investigating the behaviour of rivets, such as two-dimensional elasticity (either for cross-sections or for in-plane analysis), plate theory and full three-dimensional analyses. Here a boundary element formulation for shear-deformable plate structures joined with rivets is proposed. Several test on lap joints are presented and compared with references to show the validity and the accuracy of the present formulation. Finally, applications to stiffened aircraft structures are also presented.

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Section: Numerical Examplessupporting

confidence: 60%

Section: Introductionmentioning

confidence: 99%

Boundary element analysis of riveted aircraft panels

Pisa

Aliabadi²

2012

The Journal of Strain Analysis for Engineering Design

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“…Results are compared with [75] and are found to be in good agreement. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 The deflection w at the centre of the patch are presented in table (1).…”

Section: System Matrixmentioning

confidence: 69%

“…BEM formulation for two-dimensional riveted panels with cracks can be found in [52], while applications to riveted repairs in [54] and [70]. Widagdoo and Aliabadi in [75] analyzed the effect of different materials for composite riveted patches. The patches are added using rivets and adhesive bonding.…”

Section: Introductionmentioning

confidence: 99%

Boundary element analysis of stiffened panels with repair patches

Pisa¹,

Aliabadi²

2015

Engineering Analysis with Boundary Elements

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In this paper a boundary element method for analysis of fractured stiffened panels repaired with riveted or adhesively bonded patches is presented. In order to achieve such a formulation, several boundary element formulations involving the membrane and bending of displacement, and, stress resultants are coupled together to analyse the model. The multi-region formulation is used to simulate the stiffeners, which are modelled as an assembly. They are then connected to the sheets to form the stiffened panels by means of a rivet formulation. The dual boundary element method is used to simulate the presence of cracks, and the patches, treated as independent plates, are joined to the panel either with rivets or adhesive. A boundary element formulation for adhesive bonding is implemented to model the adhesively bonded patches. The Crack Opening Displacements (COD) method and the Jintegral are implemented to evalute the required fracture parameters. Examples presented include a wing box with a three spar section, with fully stiffened skin, and, the skin is considered to have a crack and a repair patch is used on top of the crack to stop its growth.Response to Reviewers: Thank you for highlighting the missing references and figures numbers as well as certain typo's. We have corrected all the highlighted items.Thank you for highlighting the missing references and figures numbers as well as certain typo's. We have corrected all the highlighted items. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 Detailed Response to Reviewers AbstractIn this paper a boundary element method for analysis of fractured stiffened panels repaired with riveted or adhesively bonded patches is presented. In order to achieve such a formulation, several boundary element formulations involving the membrane and bending of displacement, and, stress resultants are coupled together to analyse the model. The multi-region formulation is used to simulate the stiffeners, which are modelled as an assembly. They are then connected to the sheets to form the stiffened panels by means of a rivet formulation. The dual boundary element method is used to simulate the presence of cracks, and the patches, treated as independent plates, are joined to the panel either with rivets or adhesive. A boundary element formulation for adhesive bonding is implemented to model the adhesively bonded patches. The Crack Opening Displacements (COD) method and the J-integral are implemented to evalute the required fracture parameters. Examples presented include a wing box with a three spar section, with fully stiffened skin, and, the skin is considered to have a crack and a repair patch is used on top of the crack to stop its growth.

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“…Recently, Lingyun and Daniel (1998) analyzed two-dimensional micro-mechanical behaviors of composite materials using BEM. A new boundary element formulation for the mechanically fastened composite patch was developed by Widagdo and Aliabadi (2001). Theses works, based on forward approaches, deal with static or dynamic responses of the structural system from external conditions such as loading.…”

Section: Introductionmentioning

confidence: 99%