Thermal properties of high temperature polymer matrix fibrous composites

Morgan, Roger J.; Shin, E. Eugene; Lincoln, Jason E.

doi:10.1016/s1573-4374(02)80015-2

Cited by 13 publications

(14 citation statements)

References 6 publications

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“…Several studies on the environmental degradation of CFRPs (Nam and Seferis 1992;Bowles et al 1993Bowles et al , 1998Colin et al 2001;Morgan et al 2002;Fox et al 2004;Dao et al 2007a) reveal the variation of properties from the surface inwards because of the diffusion of oxygen through the material. Moisture enters the material at a speed determined by the material's moisture diffusivity.…”

Section: Aging Mechanismsmentioning

confidence: 99%

Environmental Degradation of Carbon Nanotube Hybrid Aerospace Composites

Barkoula

2012

Solid Mechanics and Its Applications

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This chapter focuses on the environmental response of carbon fibre-reinforced epoxy composites, where the matrix has been modified with carbon nanotubes. These newly developed hybrid aerospace systems have been recently introduced as alternatives to conventional high performance polymer composites due to their improved mechanical properties, toughness and damage sensing abilities as discussed in detail in previous chapters. First an attempt is made to outline the conditions that lead to environmental degradation specifically in aerospace environments. Next to that the response of typical aerospace composites to these environments is discussed. Following, the benefits and challenges in using hybrid aerospace composites in in-service conditions is presented. The degradation of hybrid composites due to exposure on hydro/hygrothermal loadings and galvanic corrosion is presented based on preliminary results. In this section, the focus is on epoxy based composites reinforced with carbon fibres. Matrix modification of these systems is provided by the addition of carbon nanotubes.

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Section: Aging Mechanismsmentioning

confidence: 99%

Environmental Degradation of Carbon Nanotube Hybrid Aerospace Composites

Barkoula

2012

Solid Mechanics and Its Applications

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“…Polyimides are a class of high‐temperature polymers that have found use in a variety of applications, from electronics to aerospace, because of their high thermal stability and excellent mechanical, chemical, and electrical properties [1, 2]. In addition, fiber‐reinforced, high‐temperature, polymer‐matrix composites are particularly attractive for aerospace structures because of their low density [2, 3], high mechanical strength [2, 4–10], high modulus [2, 4, 6, 8, 9], thermo‐oxidative stability [2, 4, 9, 11, 12], electrical properties [2, 6, 10, 13], and excellent chemical resistance [2, 5, 6, 14]. Various polyimide‐based composites have been studied for use in aerospace applications for these reasons [2, 4, 6, 11, 15].…”

Section: Introductionmentioning

confidence: 99%

“…This trapped moisture can lead to a reduction in strength and strain at failure because of blistering and micro‐cavitation [16, 20]. Blistering, in particular, occurs when there is enough moisture pressure to exceed the strength of the material, which happens when the temperature and water content is high [6, 17]. In general, polyimides are very thermally stable and have characteristically high T g s and decomposition temperatures [15], but their uptake of moisture needs further study, especially for fluorinated polyimides, because of initial findings with similar polyimides (PMR‐II‐50, AFR700B, and PETI‐5) [3, 16–19].…”

Section: Introductionmentioning

confidence: 99%

“…Two similar polyimides, PMR‐II‐50 and AFR700B (Scheme a and b), have been studied for use in military and aerospace applications. The amount of moisture needed to induce blistering in these neat‐resin materials is rather low (0.5 wt% for PMR‐II‐50 and 0.4 wt% for AFR700B) [3, 6, 17]. The blister temperature for both materials at these moisture levels is also low (∼315°C) [3, 6].…”

Section: Introductionmentioning

confidence: 99%

“…The amount of moisture needed to induce blistering in these neat‐resin materials is rather low (0.5 wt% for PMR‐II‐50 and 0.4 wt% for AFR700B) [3, 6, 17]. The blister temperature for both materials at these moisture levels is also low (∼315°C) [3, 6]. Both polyimides exhibit good thermal stability, but the T g for PMR‐II‐50 is 363°C and for AFR700B it is near 400°C, whereas the fluorinated polyimide used here is 435–455°C [5, 8, 15, 23].…”

Section: Introductionmentioning

confidence: 99%

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Blistering in carbon‐fiber‐filled fluorinated polyimide

et al. 2010

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A blistering study was performed on a fluorinated polyimide resin and its carbon-fiber composite in an effort to determine the blister-formation temperature and the influence of blisters on composite performance. The fluorinated resin and carbon-fiber composite exhibit higher glass-transition (435-4558C) and decomposition temperatures (above 5208C) than similar polyimide resins and their carbon-fiber composites currently used. Two techniques were used to determine moisture-induced blister formation. A transverse extensometer with quartz lamps as a heating source measured thickness expansion, as did a thermomechanical analyzer as a function of temperature. Both methods successfully measured the onset of blister formation with varying amounts of absorbed moisture (up to 3 wt%) in the samples. The polyimide resin exhibited blister temperatures ranging from 225 to 3628C, with 1.7-3.0 wt% absorbed moisture, and the polyimide composite had blister temperatures from 246 to 2948C with 0.5-1.5 wt% moisture. The blistering effects of the polyimide composites were found to have little correlation with modulus. POLYM. COMPOS., 32:185-192, 2011. ª

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Investigation of the viscoelastic response of high temperature AS4‐12K/RP46 composites using a micromechanical approach

2014

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The viscoelastic behavior of a RP46 polyimide resin is characterized at high temperature and the results are used within a micromechanical model to predict the viscoelastic response of a RP46 based carbon fiber composite. The creep master curve of the neat resin is obtained using the time temperature superposition principle (TTSP) from creep tests at three different temperatures, namely 180, 220, and 270 C. The viscoelastic behavior of RP46 is modeled based on Schapery's single integral constitutive equation whose Prony Series coefficients are obtained from the master curve. The acquired properties are then incorporated into a Simplified Unit Cell Micromechanical model to study the creep response of a RP46 resin based composite system. The advantage of this particular micromechanical model lies in its ability to give closed form expressions for the effective viscoelastic response of unidirectional composites as well as each of their constituents. Two types of nonlinearities were observed, one due to stress and the other due to temperature.

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Thermal properties of high temperature polymer matrix fibrous composites

Cited by 13 publications

References 6 publications

Environmental Degradation of Carbon Nanotube Hybrid Aerospace Composites

Environmental Degradation of Carbon Nanotube Hybrid Aerospace Composites

Blistering in carbon‐fiber‐filled fluorinated polyimide

Investigation of the viscoelastic response of high temperature AS4‐12K/RP46 composites using a micromechanical approach

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