Postbuckling and Growth of Delaminations in Composite Plates Subjected to Axial Compression

Reeder, James R.; Chunchu, Prasad B.; Song, Kyongchan; Ambur, Damodar R.

doi:10.2514/6.2002-1746

Cited by 37 publications

(31 citation statements)

References 11 publications

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“…focussed on the debonding of stitched composite structures [122][123][124]. Delamination buckling has been investigated as well using plate/shell models [56,[125][126][127][128][129].…”

Section: Applying the Virtual Crack Closure Technique To Analysis Witmentioning

confidence: 99%

Virtual crack closure technique: History, approach, and applications

Krueger

2004

Applied Mechanics Reviews

1,110

557

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports, 1215 An overview of the virtual crack closure technique is presented. The approach used is discussed, the history summarized, and insight i n to its applications provided. Equations for two-dimensional quadrilateral elements with linear and quadratic shape functions are given. Formulae for applying the technique in conjuction with threedimensional solid elements as well as plate shell elements are also provided. Necessary modi cations for the use of the method with geometrically nonlinear nite element analysis and corrections required for elements at the crack tip with di erent lengths and widths are discussed. The problems associated with cracks or delaminations propagating between di erent materials are mentioned brie y, a s w ell as a strategy to minimize these problems. Due to an increased interest in using a fracture mechanics based approach to assess the damage tolerance of composite structures in the design phase and during certi cation, the engineering problems selected as examples and given as references focus on the application of the technique to components made of composite materials. • TECHNICAL MEMORANDUM. Scientific and technical findings that are preliminary or of specialized interest, e.g., quick release reports, working papers, and bibliographies that contain minimal annotation. Does not contain extensive analysis.• CONTRACTOR REPORT. Scientific and technical findings by NASA-sponsored contractors and grantees.• CONFERENCE PUBLICATIONS. Collected papers from scientific and technical conferences, symposia, seminars, or other meetings sponsored or cosponsored by NASA.• SPECIAL PUBLICATION. Scientific, technical, or historical information from NASA programs, projects, and missions, often concerned with subjects having substantial public interest.• TECHNICAL TRANSLATION. Englishlanguage translations of foreign scientific and technical material pertinent to NASA's mission. propagating between different materials are mentioned briefly, as well as a strategy to minimize these problems.Due to an increased interest in using a fracture mechanics based approach to assess the damage tolerance of composite structures in the design phase and during certification, the engineering problems selected as examples and given as references focus on the application of the technique to components made of composite materials.

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“…focussed on the debonding of stitched composite structures [122][123][124]. Delamination buckling has been investigated as well using plate/shell models [56,[125][126][127][128][129].…”

Section: Applying the Virtual Crack Closure Technique To Analysis Witmentioning

confidence: 99%

Virtual crack closure technique: History, approach, and applications

Krueger

2004

Applied Mechanics Reviews

1,110

557

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“…This value has been estimated considering the maximum delamination length, measured via X-rays, reported in [21]. Dynamic implicit simulations of the CAI tests have been performed in ABAQUS with an imposed compressive displacement of 1.0 mm in 60 s. In each FE model a geometrical imperfection with a maximum out-of-plane displacement of the thin sublaminate equal to 0.1 mm (as suggested in [21]) is introduced. The shape of the geometrical imperfection is extracted by dedicated linear buckle simulations for each model.…”

Section: Geometrical Initialization Test-casementioning

confidence: 99%

“…The developed inter-laminar constitutive behavior, implemented in a dedicated UMAT subroutine, has been assessed by comparison with the results of a Compression After Impact (CAI) test of a carbon/epoxy specimen with a circular defect manifactured with a teflon insert [21]. The specimen has a ½ðÀ45=þ45= 90=0Þ 2 =À60=þ60=À15=þ15 s lamination with the teflon insert between the 5th and 6th ply (À45= þ 45 interface).…”

Section: Geometrical Initialization Test-casementioning

confidence: 99%

“…ABAQUS Standard (Dynamic Implicit solver) analyses were performed on test cases, of increasing complexity, in order to assess the proposed procedure for damage initialization and verify the performances of the different operating modes. The first case is relevant to an artificially damaged CAI specimen for which literature data exist about delamination buckling with stable damage growth [21]. In the second case, an impact damage scenario on a CAI specimen is reconstructed from literature information [22] and damage growth during compression is simulated numerically.…”

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confidence: 99%

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Damage initialization techniques for non-sequential FE propagation analysis of delaminations in composite aerospace structures

2015

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The experimental effort required to develop, damage tolerant, aerospace composite structures could be significantly reduced if reliable numerical simulations were used to perform engineering studies of complex damaged structures. Finite element (FE) simulations of impact damaged structures typically follow a sequential approach that require large computational resources to reproduce complex damage scenarios. A numerical tool capable to reconstruct such scenarios using data from previous impact simulations or NDI could noticeably improve the simulation workflow for damaged composite structures. The paper proposes a method to inizialize the damage variables in numerical analyses aimed at assessing damage propagation, and that are potentially able to evaluate the residual strength of damaged structures. The approach is developed within FE software ABAQUS, and uses SDVINI subroutine to initialize damage variables defined by a user-material-subroutine (UMAT), that provides the constitutive models of the lamina and of the interlaminar layers. Albeit the proposed technique might deal with both inter-laminar and intra-laminar damage, the paper is focused on delaminations. A user defined traction-separation law is coded in an UMAT that endows ABAQUS cohesive elements with damage initialization capabilities. Then, results of test cases, of increasing complexity, are presented in order to assess the damage initialization procedure and verify the performances of its different operating modes. Two test-cases are based on plate-like specimens for which literature data exist: the first is relevant to a circular artificial delamination while the second presents multiple delaminations caused by an impact and measured via NDI techniques. The last test-case is a stiffened panel which incorporates the typical complexities of aerospace structures, but is still tractable with the sequential simulation approach whose results are used as a term of comparison

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“…Mixed-mode delamination growth is predicted when mixed mode fracture energy (G T ) is greater than critical fracture energy (G C ). Several laws implemented in FEM codes have been considered to compute the fracture toughness for mixedmode failure, such as Benzeggagh-Kenane (B-K) criterion [23] the power law criterion [24], and the Reeder criterion [25]. Demonstration of applications of B-K criterion can be found in the work of Camanho et al [26] for PEEK and epoxy composites.…”

Section: Delamination Growthmentioning

confidence: 99%

Stochastic analysis of inter- and intra-laminar damage in notched PEEK laminates

Naderi¹,

Khonsari²

2013

Express Polym. Lett.

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Abstract. This paper presents a finite element model to predict the progressive damage mechanisms in open-hole PEEK (Poly-Ether-Ether-Ketone) laminates. The stochastic laminate's properties with non-uniform stress distribution are considered from element to element using the Gaussian distribution function. The failure modes considered are: fiber tension/ compression, matrix tension/compression, fiber/matrix shear, and delamination damage. The onset of damage initiation and propagation are predicted and compared with three different failure criteria: strain-based damage criterion, Hashin-based degradation approach and stress-based damage criterion which is proposed by the authors of the present work. The interlaminar damage modes associated with fiber/matrix shearing and delamination are modeled using the cohesive elements technique in ABAQUS™ with fracture energy evolution law. Mesh sensitivity and the effect of various viscous regularization factors are investigated. Damage propagation and failure path are examined by re-running the program for several times.

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Postbuckling and Growth of Delaminations in Composite Plates Subjected to Axial Compression

Abstract: The postbuckling response and growth of circular delaminations in flat and curved plates are investigated

Cited by 37 publications

References 11 publications

Virtual crack closure technique: History, approach, and applications

Virtual crack closure technique: History, approach, and applications

Damage initialization techniques for non-sequential FE propagation analysis of delaminations in composite aerospace structures

Stochastic analysis of inter- and intra-laminar damage in notched PEEK laminates

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