The Response of Fiber-Reinforced Elastomers under Simple Tension

Peel, Larry D.; Jensen, David W.

doi:10.1177/002199801772661966

Cited by 11 publications

(12 citation statements)

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“…In a vacuum assisted hand layup fabrication technique, the fibers would not be fully stretched during the fabrication of the GFRP composites process. As the strain increases, the fibers stretch and the stiffness increases accordingly as reported by others [36][37][38]. However with the increase of strain level, the damage accumulates in the matrix and initiates debonding between the matrix and the fibers.…”

Section: Tensile Strengthsupporting

confidence: 52%

Improving Fatigue Performance of GFRP Composite Using Carbon Nanotubes

Genedy

Daghash

Soliman

et al. 2015

Fibers

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Glass fiber reinforced polymers (GFRP) have become a preferable material for reinforcing or strengthening reinforced concrete structures due to their corrosion resistance, high strength to weight ratio, and relatively low cost compared with carbon fiber reinforced polymers (CFRP). However, the limited fatigue life of GFRP hinders their use in infrastructure applications. For instance, the low fatigue life of GFRP caused design codes to impose stringent stress limits on GFRP that rendered their use non-economic under significant cyclic loads in bridges. In this paper, we demonstrate that the fatigue life of GFRP can be significantly improved by an order of magnitude by incorporating Multi-Wall Carbon Nanotubes (MWCNTs) during GFRP fabrication. GFRP coupons were fabricated and tested under static tension and cyclic tension with mean fatigue stress equal to 40% of the GFRP tensile strength. Microstructural investigations using scanning electron microscopy (SEM) and Fourier Transform Infrared (FTIR) spectroscopy were used for further investigation of the effect of MWCNTs on the GFRP composite. The experimental results show the 0.5 wt% and the 1.0 wt% MWCNTs were able to improve the fatigue life of GFRP by 1143% and 986%, respectively, compared with neat GFRP.

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Section: Tensile Strengthsupporting

confidence: 52%

Improving Fatigue Performance of GFRP Composite Using Carbon Nanotubes

Genedy

Daghash

Soliman

et al. 2015

Fibers

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“…The author suggested combining the Tecoflex 80A with a woven material like Spandura ® to achieve a high strain capability and recovery rate from the polymer with the high strength from the fibres. This was achieved by Peel and Jensen and Peel et al . In these studies, they successfully manufactured silicone and urethane glass reinforced composite to a thickness of 0.8 mm using filament winding and autoclave techniques.…”

Section: Review Of Materials For Morphing Structuresmentioning

confidence: 99%

Review of morphing concepts and materials for wind turbine blade applications

2012

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With increasing size of wind turbines, new approaches to load control are required to reduce the stresses in blades. Experimental and numerical studies in the fields of helicopter and wind turbine blade research have shown the potential of shape morphing in reducing blade loads. However, because of the large size of modern wind turbine blades, more similarities can be found with wing morphing research than with helicopter blades. Morphing technologies are currently receiving significant interest from the wind turbine community because of their potential high aerodynamic efficiency, simple construction and low weight. However, for actuator forces to be kept low, a compliant structure is needed. This is in apparent contradiction to the requirement for the blade to be load carrying and stiff. This highlights the key challenge for morphing structures in replacing the stiff and strong design of current blades with more compliant structures. Although not comprehensive, this review gives a concise list of the most relevant concepts for morphing structures and materials that achieve compliant shape adaptation for wind turbine blades.Copyright © 2012 John Wiley & Sons, Ltd.

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“…Using nonlinear material properties is beyond the scope of this article but is considered in other works by the author [2,4]. This work uses only the traditional inplane orthotropic material properties E 1 , E 2 , G 12 , and ν 12 to describe the inplane axial modulus of elasticity, inplane transverse modulus of elasticity, inplane shear stiffness, and inplane major PR, respectively, in each layer of a laminate.…”

Section: Originalmentioning

confidence: 99%

“…Polyurethanes are especially popular because they bond well to the standard sizings or coatings on aerospace fibres. Silicones require special a [2], b obtained using rule of mixtures [3], c [4], d [5] fibre sizing treatments, but withstand higher temperatures than polyurethanes and tend to stiffen rather than soften when initially stretched [1]. Orthotropic and isotropic mechanical properties for selected materials of interest are presented in Table 1.…”

Section: Introductionmentioning

confidence: 99%

Exploration of high and negative Poisson's ratio elastomer‐matrix laminates

Peel

2007

Physica Status Solidi (b)

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Elastomer-matrix composites show promise for high Poisson's ratio and negative Poisson's ratio (auxetic) applications due to high orthotropy. There are approximately five orders of magnitude between the axial stiffness of high modulus graphite fibres and the stiffness of low durometer elastomers. Although the maximum Poisson's ratio for isotropic elastomers is 0.5, it is easily shown that inplane Poisson's ratios twice unity can be obtained with a graphite/epoxy angle-ply laminate at 25°. Chou and others have predicted inplane Poisson's ratios greater than 7 for certain cord-rubber combinations. Peel previously predicted inplane Poisson's ratios higher than 32 and less than -60. Preliminary experimental results have produced inplane Poisson's ratios as high as 14. Certain combinations of un-balanced highly orthotropic laminates may also produce inplane negative Poisson's ratios. Inplane Poisson's ratios, experimentally obtained from two laminate configurations with approximately the same axial stiffness are compared. A symmetric, balanced laminate produced an inplane Poisson's ratio of 3.7; while an unbalanced laminate with an equivalent axial stiffness produced an average inplane Poisson's ratio of -1.5. Certain high and negative Poisson's ratio elastomer-matrix laminates appear to have quasi anti-symmetric relationships about 0°, although laminate designers may consider dual angle-ply laminates to be the more likely counterpart to the unbalanced dual angle auxetic laminates. Unbalanced symmetric laminates experience significantly more inplane shear deformation when axially loaded than their balanced counterparts. The high shear may be desirable for damping applications, but less desirable otherwise.

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The Response of Fiber-Reinforced Elastomers under Simple Tension

Cited by 11 publications

References 0 publications

Improving Fatigue Performance of GFRP Composite Using Carbon Nanotubes

Improving Fatigue Performance of GFRP Composite Using Carbon Nanotubes

Review of morphing concepts and materials for wind turbine blade applications

Exploration of high and negative Poisson's ratio elastomer‐matrix laminates

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