Thermal effects on polymer matrix composites: Part 1. Thermal cycling

Hancox, N.L.

doi:10.1016/s0261-3069(98)00018-1

Cited by 98 publications

(74 citation statements)

References 18 publications

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“…4-5-year or 8-10-years period in vivo, respectively [23,24]. Thermocycling means a repeated cycling between two temperatures (5°C and 55°C) subject to an adequate dwell time (20 s) to ensure the thermal adjustment of the specimens without an exposure to extreme thermal stress [25].…”

Section: Discussionmentioning

confidence: 99%

Influence of plasma pretreatment on shear bond strength of self-adhesive resin cements to polyetheretherketone

et al. 2013

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OBJECTIVES: The aim of this study is to evaluate the adhesion between PEEK and two selfadhesive resin cements after plasma treatment. METHODS: Eight hundred sixty-four polyetheretherketone (PEEK) disks were cut and polished to silicon carbide (SIC) P4000. One half of the specimens were randomly selected and pretreated with plasma, whereas the remaining 432 specimens remained untreated. Subsequently, specimens were randomly allocated to four groups (n = 108/group): Visio.link (Bredent), Signum PEEK Bond (Heraeus Kulzer), Ambarino P60 (Creamed), and a control group without additional treatment. Half of the specimens of each group (n = 54) were then cemented with either RelyX Unicem Automix 2 (3 M ESPE) or with Clearfil SA (Kuraray). All specimens were stored in water for 24 h (37°C ). Afterwards, specimens were divided into three groups (n = 18) for different aging levels: (1) no aging (baseline measurement), (2) thermal aging for 5,000 cycles (5/55°C), and (3) thermal aging for 10,000 cycles (5/55°C). Thereafter, shear bond strengths (SBS) were measured, and failure types (adhesive, mixed, and cohesive) were assessed. Data were analyzed using descriptive statistics, four-and one-way ANOVA followed by a post hoc Scheffé test (p < 0.05). RESULTS: No adhesion could be established without adhesive pretreatment, irrespectively, whether plasma was applied or not. Also, no bond strength was measured when Ambarino P60 was applied. In contrast, adhesive pretreatment resulted in SBS ranging between 8 and 15 MPa. No significant differences were found between the resin cements used. In general, no cohesive failures were observed. Groups without plasma treatment combined with Visio.link or Signum PEEK Bond showed predominantly mixed failure types. Control groups, plasma treated, or treated using Ambarino P60 groups fractured predominantly adhesively. CONCLUSION: The use of methyl methacrylate (MMA)-based adhesives allows bonding between PEEK and self-adhesive resin cements. Plasma treatment has no impact on bond to resin cements. CLINICAL SIGNIFICANCE: PEEK reconstructions can be cemented using self-adhesive resin cements combined with pretreatment with MMA-based adhesives. Methods: Eight-hundred-and-sixty-four PEEK disks were cut and polished to silicon carbide (SIC) P4000. One half of the specimens was randomly selected and pre-treated with plasma, whereas the remaining 432 specimens remained untreated. Subsequently, specimens were randomly allocated to four groups (n=108/group): Visio.link (Bredent), Signum PEEK Bond (Heraeus Kulzer), Ambarino P60 (Creamed) and a control group without additional treatment. Half of the specimens of each group (n=54) were then cemented with either RelyX Unicem Automix 2 (3M ESPE) or with Clearfil SA (Kuraray).All specimens were storage in water for 24 h (37°C). Afterwards, specimens were divided into three groups (n=18) for different aging levels: i. no aging (baseline measurement), ii.thermal aging for 5000 cycles (5/55°C) and iii. thermal aging for 10000 cycles (5/55°C).Thereafte...

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Section: Discussionmentioning

confidence: 99%

Influence of plasma pretreatment on shear bond strength of self-adhesive resin cements to polyetheretherketone

et al. 2013

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“…Differential in the coefficient of thermal expansion (CTE) is a primary cause of thermal shock in composite materials, in which carbon fiber and polymeric matrix have a large difference in values, thus contributing to stresses at the interface, and moreover, a thermal shock which is related to rapid temperature changes, high temperatures, and stress gradients 1,2 . A very large CTE mismatch may result in debonding at the fiber/matrix interface and/or possible matrix cracking due to thermal stresses 2,3 .…”

Section: Introductionmentioning

confidence: 99%

“…The performance of fiber reinforced composite is often controlled by the chemical adhesion at the fiber/matrix interface 4 . Thermal cycling can be defined as changes in the temperature of the specimen when it reaches its equilibrium 1 . The temperature changes in a laminate generate stresses that can be predicted by Equation 1, one of the mostly used expressions.…”

Section: Introductionmentioning

confidence: 99%

“…The temperature changes in a laminate generate stresses that can be predicted by Equation 1, one of the mostly used expressions. Simplifying Equation 1, considering a cross ply laminate, with subscription L as the reinforcement, and by cooling the composite will induce to a compressive stress (σ L ) [1] .…”

Section: Introductionmentioning

confidence: 99%

“…This behavior yields intraply concentration stress, which is developed because of the difference of the cure and the operational temperature that requires further investigation. The aforementioned situation involves several types of interface among them there are fiber, matrix or micromechanical features [1][2][3][4][5] . A better understanding of interfacial properties and a characterization of interfacial adhesion strength can help to evaluate the mechanical behavior of fiber reinforced composite materials.…”

Section: Introductionmentioning

confidence: 99%

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Assessment of cumulative damage by using ultrasonic C-scan on carbon fiber/epoxy composites under thermal cycling

Shiino¹,

Faria²,

Botelho³

et al. 2012

Mat. Res.

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In recent years, structural composites manufactured by carbon fiber/epoxy laminates have been employed in large scale in aircraft industries. These structures require high strength under severe temperature changes of -56° until 80 °C. Regarding this scenario, the aim of this research was to reproduce thermal stress in the laminate plate developed by temperature changes and tracking possible cumulative damages on the laminate using ultrasonic C-scan inspection. The evaluation was based on attenuation signals and the C-scan map of the composite plate. The carbon fiber/epoxy plain weave laminate underwent temperatures of -60° to 80 °C, kept during 10 minutes and repeated for 1000, 2000, 3000 and 4000 times. After 1000 cycles, the specimens were inspected by C-scanning. A few changes in the laminate were observed using the inspection methodology only in specimens cycled 3000 times, or so. According to the found results, the used temperature range did not present enough conditions to cumulative damage in this type of laminate, which is in agreement with the macro -and micromechanical theory.

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Polyoxymethylene Additives

Richaud¹

2014

Polyoxymethylene Handbook

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Thermal effects on polymer matrix composites: Part 1. Thermal cycling

Cited by 98 publications

References 18 publications

Influence of plasma pretreatment on shear bond strength of self-adhesive resin cements to polyetheretherketone

Influence of plasma pretreatment on shear bond strength of self-adhesive resin cements to polyetheretherketone

Assessment of cumulative damage by using ultrasonic C-scan on carbon fiber/epoxy composites under thermal cycling

Polyoxymethylene Additives

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