Impact damage prediction and failure analysis of heavily loaded, blade-stiffened composite wing panels

Wiggenraad, J.F.M.; Zhang, Xiang; Davies, G. A. O.

doi:10.1016/s0263-8223(98)00132-9

Cited by 37 publications

(27 citation statements)

References 5 publications

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“…Sometimes, it is even possible to observe the propagation of delamination due to this buckling [13,18,26,27]. The majority of researchers agree that, indeed, the buckling (especially local buckling) plays a key role in the final rupture [13,15,18,[25][26][27][28][29][30][31]. However, this phenomenon is not sufficient to explain the final failure of the structure, since in most cases the delamination does not propagate over the entire width of the plate, and the final rupture is due to the sudden propagation of a crack from the impact zone to the edges of the structure.…”

Section: Introductionmentioning

confidence: 99%

Experimental analysis of CFRP laminates subjected to compression after impact: The role of impact-induced cracks in failure

Rivallant

Bouvet

Abdallah

et al. 2014

Composite Structures

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Section: Introductionmentioning

confidence: 99%

Experimental analysis of CFRP laminates subjected to compression after impact: The role of impact-induced cracks in failure

Rivallant

Bouvet

Abdallah

et al. 2014

Composite Structures

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“…Other notable works on the subject were those of Wu and Yang [176] and Kant and Mallikarjuna [78]. Transient analyses with damage of composites in recent studies are mostly focused on impact response, such as works by Wiggenraand et al [171] and Geubelle and Baylor [50].…”

Section: Laminate Composite Progressive Failurementioning

confidence: 99%

Nonlinear Formulations of a Four-Node Quasi-Conforming Shell Element

Lomboy

Suthasupradit

Kim

et al. 2009

Arch Computat Methods Eng

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The quasi-conforming technique was introduced in the 1980's to meet the challenge of inter-elements conforming problems and give a unified treatment of both conforming and nonconforming elements. While the linear formulation is well established, the nonlinear formulation based on the quasi-conforming technique that includes geometric and material nonlinearity is presented in this paper. The formulation is derived in the framework of an updated Lagrangian stress resultant, co-rotational approach. The geometric nonlinear formulation provides solutions to buckling and postbuckling behaviour while the material nonlinear formulation considers the spread of plasticity within the element while maintaining an explicit construction of element matrices. Aside from the elasto-plastic constitutive relation, formulations on laminate composites and reinforced concrete are also presented.The formulations of laminate composite and reinforced concrete material are present based on the layer concept, the material properties can vary throughout the thickness and across the surface of a shell element. The various failure criteria for laminate composite are included in the formulation which makes it possible to analyses the progressive failure of fibre and matrix. For the reinforced concrete material, the nonlinearities as a result of tensile cracking, tension stiffening between cracks, the nonlinear response of concrete in compression, and the yielding of the reinforcement are considered. The steel reinforcement is modeled as a bilinear material with strain hardening.

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“…Impact induced delamination onset and evolution, can also be influenced by the impact location, especially in complex composite laminated structures characterized by a non-uniform material distribution and by relevant geometrical discontinuities (stiffened panels, etc.) [17].…”

Section: Introductionmentioning

confidence: 99%

Impact Damage Management of Composite Laminated Structures by a Probabilistic Approach

Riccio¹,

Russo²,

Scaramuzzino³

2013

TOMSJ

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A numerical procedure for the design of impact damage resistant composite laminated structures is proposed in the present paper. This procedure, based on probabilistic analyses, is able to support the design of complex composite laminated structures by accounting for the scatter in composite materials' mechanical properties (related to the mutable environmental conditions experienced by an aircraft component during its service life) and by accounting for the uncertainty on accidental impacts locations. A failure criterion, based on the determination of the threshold critical impact energy for impact induced delaminations' onset, is adopted for the evaluation of the damage resistance of composite laminated structures, in the frame of the introduced probabilistic analyses.The proposed procedure has been implemented into a commercial FEM platform and composite panels have been used as numerical benchmarks to investigate the influence of the combined material properties and impact location uncertainties on composite laminated structures' impact damage resistance. A further comparison between two different stiffened composite panels designs have been introduced to highlight the added value of the proposed impact damage resistance probabilistic approach in terms of safety and effectiveness, with respect to the standard deterministic tools.

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Impact damage prediction and failure analysis of heavily loaded, blade-stiffened composite wing panels

Cited by 37 publications

References 5 publications

Experimental analysis of CFRP laminates subjected to compression after impact: The role of impact-induced cracks in failure

Experimental analysis of CFRP laminates subjected to compression after impact: The role of impact-induced cracks in failure

Nonlinear Formulations of a Four-Node Quasi-Conforming Shell Element

Impact Damage Management of Composite Laminated Structures by a Probabilistic Approach

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