Compression after impact behavior of carbon/epoxy composite sandwich panels with Nomex honeycomb core subjected to low velocity impacts at extreme cold temperatures

Jean-St-Laurent, Mathilde; Dano, Marie‐Laure; Potvin, Marie-Josée

doi:10.1016/j.compstruct.2020.113516

Cited by 12 publications

(9 citation statements)

References 35 publications

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“…For this impact condition, there are two main damage modes for the composite skin: fiber breakage and delamination. Previous tests, performed by the same research group, on the effect of extreme cold temperatures on the mechanical behavior of composite laminates showed that the tensile strength is negatively affected by cold temperatures [4], which could be an explanation for the more severe damages at cold temperatures. As for the delamination, studies have looked at the effect of extreme cold temperatures on delaminations under mode I and II [6–10].…”

Section: Discussionmentioning

confidence: 99%

“…The effect of temperature on the out-of-plane compressive behavior of the Nomex core has been studied by the same research group [4]. The results of the study show an increase in out-of-plane compressive modulus, as well as maximum out-of-plane compressive strength, at cold temperatures.…”

Section: Discussionmentioning

confidence: 99%

“…All of the components of the sandwich panels were chosen because they fulfilled space application requirements. The properties of the composite skins were characterized at room temperature, −70°C, −130°C, and/or −150°C [4].…”

Section: Materials and Specimen Geometrymentioning

confidence: 99%

“…Studies have shown that in-plane shear modulus and in-plane shear strength increase at low temperatures [2–4] as well as the interlaminar shear strength [5,6]. Kumagai et al.…”

Section: Introductionmentioning

confidence: 99%

“…Jean-St-Laurent et al. [4] investigated the effect of temperature on woven carbon/epoxy laminates under tension and compression loadings. They observed that while tensile strength decreases at cold temperatures, compressive strength increases.…”

Section: Introductionmentioning

confidence: 99%

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Effect of extreme cold temperatures on quasi-static indentation and impact behavior of woven carbon fiber epoxy composite sandwich panels with nomex honeycomb core

Jean-St-Laurent

Dano

Potvin

2021

Jnl of Sandwich Structures & Materials

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The effect of extreme cold temperatures on the quasi-static indentation and the low velocity impact behavior of woven carbon/epoxy composite sandwich panels with Nomex honeycomb core was investigated. Impact tests were performed at room temperature, –70°C, and –150°C. Two sizes of hemispherical impactor were used combined to three different impactor masses. All the impact tests were performed at the same initial impact velocity. The effect of temperature on the impact behavior is investigated by studying the load history, load-displacement curves and transmitted energy as a function of time curves. Impact damage induced at various temperatures was studied using different non-destructive and destructive techniques. Globally, more damages are induced with impact temperature decreasing. The results also show that the effect of temperature on the impact behavior is function of the impactor size.

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Section: Discussionmentioning

confidence: 99%

Section: Discussionmentioning

confidence: 99%

Section: Materials and Specimen Geometrymentioning

confidence: 99%

“…Studies have shown that in-plane shear modulus and in-plane shear strength increase at low temperatures [2–4] as well as the interlaminar shear strength [5,6]. Kumagai et al.…”

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Effect of extreme cold temperatures on quasi-static indentation and impact behavior of woven carbon fiber epoxy composite sandwich panels with nomex honeycomb core

Jean-St-Laurent

Dano

Potvin

2021

Jnl of Sandwich Structures & Materials

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Experimental and numerical investigation on compression after impact behavior of hygrothermal aged CFRP laminates

Huang

Xie

et al. 2022

Polymer Composites

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In the paper, a detailed experimental and numerical investigation of compression after impact (CAI) behavior of hygrothermal aged T300 985LV carbon/ epoxy composites is presented. Rectangular fabric laminates are damaged by low-velocity impact, and moisture absorption conditioning is carried out. The moisture absorption curves agree with Fick's law, with a moisture equilibrium rate of 0.84% at 1392 h. Then, CAI experiments are carried out on moisture saturated specimens at different temperatures. The effects of hygrothermal environments on CAI strength are obtained with an interpretation of corresponding mechanism. Furthermore, finite element analysis based on hygrothermal mechanics formulation and incremental Newton-Raphson mixed iteration equation is established. The numerical results are in good agreement with the experimental ones, with an accuracy of up to 92%, which demonstrates the effectiveness of the established numerical model. The results show that the CAI strength of 85 RH% hygroscopic saturated laminates is decreased by approximately 12% at 85 C and 17% at 128 C. Additionally, the allowable compression value of 3546 μϵ is obtained for T300 985LV composite laminates, which is useful for applications in civil aircraft design. K E Y W O R D Scompression after impact, finite element analysis, hygrothermal aged, impact damage, moisture absorption | INTRODUCTIONCarbon fiber reinforced plastic (CFRP) is widely used in aerospace, marine and other engineering industries. [1,2] Compared with conventional materials, CFRP is characterized by the advantages of high specific strength, high specific stiffness, and excellent fatigue characteristics. [3][4][5][6][7] The percentage of CFRP used in civil aircraft ranges from 25% for the A380 to 50% for the later B787, which indicates that the usage of composite is increasing in primary components for aircraft structures. [8] Since the environment that the composite structure is exposed to significantly affect its performance, it must be accounted for during design. The most important aspect of the CFRP is temperature and moisture (hygrothermal), [9][10][11][12] which are crucial for understanding these effects and considering them in composite design. In addition, the impact damage is another factor that significantly affects composite properties. The impacts (i.e., tool drop, runway gravel, and hail) cause through-thickness stress waves in

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Comparison of Tensile Properties of Carbon/Epoxy Composite Materials with Different Fiber Orientation Using Digital Image Correlation

Jelić

Travica

Ugrinović

et al. 2021

Current Problems in Experimental and Computational Engineering

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Due to its remarkable qualities, carbon fiber epoxy composite sandwich panels are used in a variety of engineering applications. The goal of this research is to use tensile testing and a full-field non-contact 3D Digital Image Correlation (DIC) method to characterize carbon fiber reinforced composite sandwich panels with varied fiber orientations (0°/90°and ± 45°). The tested materials were composed of carbon fiber prepregs with epoxy resin systems and Aramid synthetic fiber. The properties of the materials were determined using full-field data derived from 3D DIC measurements and a set of experiments by according to ASTM standards. Values of maximum stress and strain at entire areas, break stress and strain, and toughness at entire areas and, modulus of elasticity of both structures were compared. The adherend's full-field, out-of-plane deformation, strain distribution, and strain evolution along the bond line were captured using a digital image correlation method, allowing the fracture mechanism to be visually defined. Since DIC produces the displacement field, the strain field must be deduced from it. The orientation of the fibers had a significant impact on the tensile properties of the tested materials. The results revealed that the specimen with 0°/90°fiber orientation had higher break stress and brittle fracture, whereas the specimen with ± 45°fiber orientation twisted in the fiber direction had higher elongation values while carrying the applied load. In order to complement previously obtained results, scanning electron microscopy (SEM) analysis of the fibers and core, as well as fracture surfaces was performed.

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Compression after impact behavior of carbon/epoxy composite sandwich panels with Nomex honeycomb core subjected to low velocity impacts at extreme cold temperatures

Cited by 12 publications

References 35 publications

Effect of extreme cold temperatures on quasi-static indentation and impact behavior of woven carbon fiber epoxy composite sandwich panels with nomex honeycomb core

Effect of extreme cold temperatures on quasi-static indentation and impact behavior of woven carbon fiber epoxy composite sandwich panels with nomex honeycomb core

Experimental and numerical investigation on compression after impact behavior of hygrothermal aged CFRP laminates

Comparison of Tensile Properties of Carbon/Epoxy Composite Materials with Different Fiber Orientation Using Digital Image Correlation

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