Effective ply and constituent elastic properties for cracked laminates

Akula, Venkata M. K.; Garnich, Mark R.

doi:10.1016/j.compositesb.2012.02.034

Cited by 15 publications

(5 citation statements)

References 27 publications

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“…Fracture resistance of these components is relatively low, nevertheless, by their combination in a multilayer structure (containing tensile / compressive residual stresses), a significant increase of the apparent fracture toughness can be achieved -see e.g. [10].…”

Section: Apparent Fracture Toughness Of the Multilayer Compositementioning

confidence: 99%

Optimization of Design Parameters of Fracture Resistant Piezoelectric Vibration Energy Harvester

Majer

Ševeček

Machů

et al. 2018

KEM

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This paper is focused on an analysis of a multilayer ceramic-based piezoelectric vibration energy harvester, which could be excited by ambient vibrations or external forces and thus provide a useful source of electricity for modern electronics. The proposed multilayer concept of the energy harvester enables introduction of tensile / compressive residual stresses inside particular layers. These stresses are intended to be used for enhancement of the harvester ́s fracture resistance and simultaneously for the improvement of the energy gain upon its operation. A crack arrest, by means of compressive residual stresses (in the outer “non-piezo” layer), will be utilized to this end. Primarily, the extended classical laminate theory (taking into account the piezoelectric characteristics of selected layers) will be used to define various designs of particular layers with various levels of residual stresses inside them. The weight function method is subsequently employed to select a design, which is most resistant to propagation of preexisting cracks. Selected laminate configurations are verified by means of FE simulations. Such analysis is essential for development of new energy harvesting systems formed of new smart materials and structures, which could be integrated in future development processes.

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Section: Apparent Fracture Toughness Of the Multilayer Compositementioning

confidence: 99%

Optimization of Design Parameters of Fracture Resistant Piezoelectric Vibration Energy Harvester

Majer

Ševeček

Machů

et al. 2018

KEM

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“…The influence of interacting cracks has been extensively addressed in the literature with the assumption of a linear elastic material. 20,37 Determining the local stress field between existing cracks is necessary to evaluate the influence of the stress perturbation on the transferable load. For CFRP, an NCS limit of 2.5 was derived in Lundmark and Varna 17 from linear elastic FE studies with noninteracting cracks.…”

Section: Discrete Crack Analysismentioning

confidence: 99%

“…However, it is very difficult to determine experimentally the stiffness reduction of a composite laminate. 14,15 Several authors used an analytical 16–19 or a numerical approach, with representative periodic cells 14,20–23 representing the pattern of through-thickness cracks, to predict the damage effects. The results of the discrete approaches are used to define the stiffness reduction due to multiple ply cracking in the homogenized continuum damage framework.…”

Section: Introductionmentioning

confidence: 99%

Influence of nonlinear material behavior on the effect of inter-fiber cracks in composite laminates

Taubert

Mandel

Hartmann

2017

Journal of Composite Materials

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This paper presents a numerical study evaluating the influence of nonlinear material behavior on the stiffness reduction due to inter-fiber cracks. It is shown that the relation between crack density and damage variables changes as the load level increases. A three-dimensional nonlinear material model is used in a representative volume element study to accurately calculate the local stress distribution around cracks. The studies show that as the load increases the stress recovers to the far-field level within a shorter distance, and consequently the plastic deformation causes a decrease in the crack-induced stiffness reduction. To provide damage variables for a coupled elastoplastic-damage material approach at the homogenized ply level, the results of a systematic representative volume element study are used for interpolation. For verification, the response curves of several laminates influenced by inter-fiber cracks are simulated and compared to experimental results. The presented procedure enables the constitutive laminate response under large deformations to be accurately predicted.

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“…The unidirectional carbon fiber fabric was used as additional materials. The orientation angle of carbon fiber fabric moves limits are put as −90 to 90 in the analysis model [19]. The thickness of one layer was 0.2 mm.…”

Section: Optimization Of Error Calibrationmentioning

confidence: 99%

A Precise Manufacturing Method of the Composite Structure-Similar Flutter Model

Yang

Sun

Qian

et al. 2014

Advances in Mechanical Engineering

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The composite structure-similar flutter model (ComSSM) not only shows higher structural efficiency but also provides convenience for the purpose of fabrication in the aerodynamic flutter model. The manufacturing process of ComSSM is different from conventional composites structures. The geometry parameters and nongeometry parameters of ComSSM need to be controlled cooperatively and precisely to obtain higher product quality. A method of precise manufacturing is developed based on the error calibration of nongeometry parameters. The accuracy of structural performance of ComSSM is ensured by reducing the manufacturing stiffness, controlling the error of mechanical performance, and calibrating the error of modal frequency.

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Effective ply and constituent elastic properties for cracked laminates

Cited by 15 publications

References 27 publications

Optimization of Design Parameters of Fracture Resistant Piezoelectric Vibration Energy Harvester

Optimization of Design Parameters of Fracture Resistant Piezoelectric Vibration Energy Harvester

Influence of nonlinear material behavior on the effect of inter-fiber cracks in composite laminates

A Precise Manufacturing Method of the Composite Structure-Similar Flutter Model

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