Preparation and Dynamic Mechanical Analysis of Glass or carbon Fiber/Polymer Composites

Karvanis, Konstantinos; Rusnáková, Soňa; Žaludek, Milan; Čapka, Alexander

doi:10.1088/1757-899x/362/1/012005

Cited by 17 publications

(4 citation statements)

References 12 publications

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“…Since the shift factor obtained in the previous acceleration test was mainly due to the post-curing of the polymer matrix, it was necessary to confirm whether this shift factor can be applied to different orientations with the same fiber volume fraction. For this reason, the storage modulus obtained from validation tests was lower than that from acceleration test and the glass transition temperature was also decreased, as reported in a literature [56]. It was confirmed that the prediction model based on acceleration test can be applied to polymer composite regardless of fiber orientation because there was no significant difference the five validation sets.…”

Section: Quantitative Analysis Of the Ao Effect On Long-term Propertiessupporting

confidence: 81%

Accelerated Testing Method for Predicting Long-Term Properties of Carbon Fiber-Reinforced Shape Memory Polymer Composites in a Low Earth Orbit Environment

et al. 2021

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Carbon fiber-reinforced shape memory polymer composites (CF-SMPCs) have been researched as a potential next-generation material for aerospace application, due to their lightweight and self-deployable properties. To this end, the mechanical properties of CF-SMPCs, including long-term durability, must be characterized in aerospace environments. In this study, the storage modulus of CF-SMPCs was investigated in a simulation of a low Earth orbit (LEO) environment involving three harsh conditions: high vacuum, and atomic oxygen (AO) and ultraviolet (UV) light exposure. CF-SMPCs in a LEO environment degrade over time due to temperature extremes and matrix erosion by AO. The opposite behavior was observed in our experiments, due to crosslinking induced by AO and UV light exposure in the LEO environment. The effects of the three harsh conditions on the properties of CF-SMPCs were characterized individually, using accelerated tests conducted at various temperatures in a space environment chamber, and were then combined using the time–temperature superposition principle. The long-term mechanical behavior of CF-SMPCs in the LEO environment was then predicted by the linear product of the shift factors obtained from the three accelerated tests. The results also indicated only a slight change in the shape memory performance of the CF-SMPCs.

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Section: Quantitative Analysis Of the Ao Effect On Long-term Propertiessupporting

confidence: 81%

Accelerated Testing Method for Predicting Long-Term Properties of Carbon Fiber-Reinforced Shape Memory Polymer Composites in a Low Earth Orbit Environment

et al. 2021

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“…They have been widely used in many areas such as aerospace, marine, automotive, medical, sports, machine tools, and for several other structures [ 3 ]. E-glass fiber/epoxy resin prepreg is an intermediate for the manufacture of composite materials [ 4 ]. It is a composition obtained by impregnating E-glass fiber or fabric with epoxy resin.…”

Section: Introductionmentioning

confidence: 99%

The Curing Kinetics of E-Glass Fiber/Epoxy Resin Prepreg and the Bending Properties of Its Products

et al. 2021

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The curing kinetics can influence the final macroscopic properties, particularly the three-point bending of the fiber-reinforced composite materials. In this research, the curing kinetics of commercially available glass fiber/epoxy resin prepregs were studied by non-isothermal differential scanning calorimetry (DSC). The curing kinetic parameters were obtained by fitting and the apparent activation energy Ea of the prepreg, the pre-exponent factor, and the reaction order value obtained. A phenomenological nth-order curing reaction kinetic model was established according to Kissinger equation and Crane equation. Furthermore, the optimal curing temperature of the prepregs was obtained by the T-β extrapolation method. A vacuum hot pressing technique was applied to prepare composite laminates. The pre-curing, curing, and post-curing temperatures were 116, 130, and 153 °C respectively. In addition, three-point bending was used to test the specimens’ fracture behavior, and the surface morphology was analyzed. The results show that the differences in the mechanical properties of the samples are relatively small, indicating that the process settings are reasonable.

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“…This increased motion lowers the temperature at which the glass matrix starts becoming rubbery (i.e., glass transition temperature, T g ) 13–15,19,49–56 . Dynamic mechanical analysis (DMA) can be used to measure T g and the change of T g with fuel absorption by the composites 55–62 . DMA provides storage modulus ( E' ), loss modulus ( E" ), and tan( δ ) (= E" / E' ) as a function of temperature and frequency.…”

Section: Introductionmentioning

confidence: 99%

“…[13][14][15]19,[49][50][51][52][53][54][55][56] Dynamic mechanical analysis (DMA) can be used to measure T g and the change of T g with fuel absorption by the composites. [55][56][57][58][59][60][61][62] DMA provides storage modulus (E'), loss modulus (E"), and tan(δ) (=E"/E') as a function of temperature and frequency. E' represents the ability of a material to store energy, whereas E" measures the energy dissipation.…”

Section: Introductionmentioning

confidence: 99%

Effects of cyclic absorption–desorption of model fuels by aerospace‐grade carbon/epoxy composites

et al. 2023

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The aviation industry is in the process of using several alternative fuels sourced from renewable sources to decrease its impact on the environment. These alternative fuels are mostly comprised of aliphatic hydrocarbons and have low to no aromatic content. The Federal Aviation Administration (FAA) has approved several drop‐in fuels, in which alternative fuels are typically blended with conventional Jet A fuel. Because of blending, the drop‐in fuels consist of both aliphatic and aromatic components. To achieve a fundamental understanding of how individual aliphatic and aromatic components interact with the aerospace‐grade composites, we have considered four model fuels, three aliphatic with varying chain lengths and one aromatic. The absorption of these model fuels by composites in three absorption/desorption cycles was captured and compared to the conventional Jet A fuel. The equilibrium weight gain by the composites due to absorption was low but was different for each model fuel, and the trend could be validated using Hansen solubility parameters. The absorption of model fuels decreased the glass transition temperature of composites. The change in glass transition temperature was not significantly different between the model fuels and the conventional fuel. These results can be translated to alternative fuels, making them a possible substitute for Jet A in the aviation industry.

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Preparation and Dynamic Mechanical Analysis of Glass or carbon Fiber/Polymer Composites

Cited by 17 publications

References 12 publications

Accelerated Testing Method for Predicting Long-Term Properties of Carbon Fiber-Reinforced Shape Memory Polymer Composites in a Low Earth Orbit Environment

Accelerated Testing Method for Predicting Long-Term Properties of Carbon Fiber-Reinforced Shape Memory Polymer Composites in a Low Earth Orbit Environment

The Curing Kinetics of E-Glass Fiber/Epoxy Resin Prepreg and the Bending Properties of Its Products

Effects of cyclic absorption–desorption of model fuels by aerospace‐grade carbon/epoxy composites

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