Analysis of Composite-Reinforced Cutouts and Cracks

Mitchell, Richard A.; Woolley, Ruth M; Chwirut, Daniel J.

doi:10.2514/3.60431

Cited by 32 publications

(7 citation statements)

References 3 publications

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“…The general approach used here parallels one used earlier for the planform analysis of composite-reinforced cutouts and cracks [2,3]. Figure 3(a) shows the network of triangular finite elements used for the analysis of the weldbonded joint shown in Figure 1 and a similar spotwelded joint.…”

Section: Planform Analysismentioning

confidence: 99%

Component parts assembly with joints. Adhesive-mechanical Part 4. Analysis and test of bonded and wellbonded lap joints

Mitchell¹,

Woolley²,

Baker³

1976

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In Block 20, If different from Report) 18. SUPPLEMENTARY NOTES 19. KEY WORDS (Continue on reverse side if necessary and Identify by block number) Adhesive-bonded joints; bonded joints; cyclic loading; debond analysis; double-lap-joint analysis; fatigue tests; finite element analysis; joints; nonlinear analysis; single-lap-joint analysis; single-lap-joint bending; spotwelded joints; weldbonded joints. 20. ABSTRACT ("Cotrtfotie on rvvers* sftto If n*ce^aaiy aad Identify by block number) Finite element computer techniques were used to study the linear and nonlinear structural response of bonded and weldbonded lap joints. Although the techniques used are applicable to either single-lap or doublelap joints, the emphasis was on the single-lap joint problem with the attendant complication of joint bending. Nonlinear algorithms were developed to account for nonlinear stress-strain characteristics of the adhesive, and the joined metal .^heet, weld-heat softening of the metal sheet, progressive debonding of the DO , j^^Ta 1473 EDfTlOM OF » MOV 65 IS OBSOLETE Unclassified SECURITY CLASSIFICATtON OF THIS PAGE (When Data Entered) Unrlassif led SECURITY CLASSIFICATION OF THIS PAGECl*TiBn Data Entered) 20. Abstract (continued) adhesive, and nonlinear cyclic loading. The nonlinear modes of response were simulated by sequences of linear solutions. Eight different single-lap joint configurations, designed so as to constitute an experimental parameter study, were studied in a laboratory testing program. Representative specimens were subjected to quasi-static tensile strength and cyclic-load tests and to tensile fatigue tests. The quasi-static and fatigue data generally plot into clear S-N patterns that are in a reasonable relationship to the lap joint design parameters. For the most part, strains measured on the surfaces of the test specimens were in reasonably good agreement with those computed by finite element analysis, provided out-ofplane bending effects were accounted for. The dominant failure modes were consistent with the computer analyses. Unclassified SECURITY CLASSIFICATION OF THIS P ACECWhen Data Entered)

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Section: Planform Analysismentioning

confidence: 99%

Component parts assembly with joints. Adhesive-mechanical Part 4. Analysis and test of bonded and wellbonded lap joints

Mitchell¹,

Woolley²,

Baker³

1976

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“…Especially, it was pointed out that SIF at the crack tip as fracture parameter is important for the prediction of the extent of improved performance of a bonded composite repair. The analytical investigations were primarily based on the finite element method, namely Ayatolahi and Hashemi [6], Mitchel et al [7], Jones and Callinan [8], Ting et al [9], Bouiadjra et al [10], Umamaheswar and Singh [11].…”

Section: Introductionmentioning

confidence: 99%

Analysis of cracked aluminum plates with one-sided patch repair using p-convergent layered model

Ahn

Basu

Woo

2010

Finite Elements in Analysis and Design

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“…Analytically, several works have been devoted to understanding this class of problems represent the effect of the patch on the crack tip stress intensity factor such as, Mitchell and al. [3], Jones and Callinan [4], Rose [5 -7], Young and al. [8,9], Rooke and al [10], Ramesh Chandra and al., [11] Liu and Fan [12], Arendt and Sun [13].…”

Section: Introductionmentioning

confidence: 99%

Analysis of the crack-crack interaction effect initiated in aeronautical structures and repaired by composite patch

Ibrahim¹,

Sérier²,

Mechab³

2018

Frattura Ed Integrità Strutturale

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In this work, we analyze three -dimensionally, by the finite element method, the performance of the repair of aeronautical structures damaged by cracking and repaired by patch of composite materials. The effect of crack-crack interaction according to their position and interdistance was analyzed. The criterion of rupture retained for this study is the factor of intensity of constraints. We show that this factor increases considerably and reaches a critical threshold when the two cracks develop towards each other. The repair of such damage using a composite patch ensures the stability of this structure during the commissioning process. The sharp fall in the stress intensity factor is characteristic of this stability.

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Analysis of Composite-Reinforced Cutouts and Cracks

Cited by 32 publications

References 3 publications

Component parts assembly with joints. Adhesive-mechanical Part 4. Analysis and test of bonded and wellbonded lap joints

Component parts assembly with joints. Adhesive-mechanical Part 4. Analysis and test of bonded and wellbonded lap joints

Analysis of cracked aluminum plates with one-sided patch repair using p-convergent layered model

Analysis of the crack-crack interaction effect initiated in aeronautical structures and repaired by composite patch

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