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Thermal and rheological testing was carried out on prepregs produced with two different commercial epoxy resins - M2100ae and 8552, respectively, with the intention to investigate and optimize the curing cycle of structural components used in aerospace industry. The lowest heating rates for processing both materials were found to be the lower ones, according to the researchers, as they allow for a better understanding of chemical reactions involved and physical changes that are normal during curing process stages. The recommended curing cycle from the supplier is the correct option for the materials involved, according to analytically.
The novel aligned polyvinylene fluoride green core'u2013shell nanofibers were added to carbon fiber/epoxy prepregs and were made using the vacuum bagging process. The components of the EDX analysis revealed the fragments of the fractured healing carriers' resin and hardener. With the addition of nanofibers, the mechanical properties of self-healing composites were determined by tensile, flexural, and Izod impact tests, revealing an increase in both flexural and impact strength. Overall, the research results showed a range of eco-friendly carriers for carbon fiber-reinforced composites with the ability of good self-healing characteristics without losing the mechanical integrity.
Source link: https://doi.org/10.1515/ntrev-2022-0110
The effect of such surface modification techniques on the mechanical properties of the mechanical properties was also investigated. The interfacial hear strength of MXene functionalized CF increased by 36. 5 percent over untreated CF, up 33. 5%, although the tensile strength was not reduced. The interfacial enhancement process could be the result of the tight structure and high surface area of MXene's high surface activity.
Source link: https://doi.org/10.1016/j.jmrt.2022.06.101
This novel review provides the first non-destructive three-dimensional visualization of resin deformation behavior around crack tips, as well as valuable and unique advice for future CFRP design.
Source link: https://doi.org/10.1016/j.dib.2020.105894
Concerns regarding the UV tenacity of carbon fiber composites have arisen. UV irradiation on carbon fiber-reinforced polymer composites was investigated in this study by an artificially accelerated UV age chamber to investigate the effect of UV exposure on carbon fiber composites. The CFRP specimens were characterized by nanoindentation, and it was found that UV aging had an embrittlement effect on the matrix, and its hardness/modulus values were higher than those with UV exposure, which were higher than initial values.
Source link: https://doi.org/10.3390/ma15082919
Using experimental and numerical simulation techniques, this research investigated the effect of temperature on the interfacial shear strength of carbon fiber and epoxy resin matrices under various thermal loads. IFSS values of CF/EP have decreased dramatically when the temperature hits near glass transition temperature, as shown by the experimental results. The results showed that temperature dependence of IFSS is correlated to the modulus of the matrix as well as the coefficients of thermal expansion of the fiber and matrix.
Source link: https://doi.org/10.1155/2018/3206817
The effects of thermoplastic polyimide and polypropylene fibers and isal density of the toughened layer on interlaminar fracture hardness and impact of carbon fiber/epoxy laminated composites were investigated. The interlaminar fracture hardness of Mode I was determined by two cantilever beam tests. Overall, the impact of low velocity impact on CF/EP laminated composites, G IC and G IIC were up by 98. 47% and 84. 07%, respectively, and F max and E were up by 92. 8 percent and 299. 08% under low velocity impact.
Source link: https://doi.org/10.3390/molecules24183367
The maximum value of 1520. 3 MPa, flexural response, modular modulus, and interlaminar shear strength of AMGNS-MWCNT composites, which were 12. 5%, 9. 42%, and 10. 1% higher than that of carbon fiber reinforced epoxy unidirectional composites at the time, was 0. 9 percent, 9. 42%, and 10. 1% higher than that of carbon fiber reinforced epoxy unidirectional composites.
Source link: https://doi.org/10.3390/nano10091670
Processing optimization is a critical way to reduce manufacturing defects in a cost-effective manner. However, processing optimization in high-speed automated fiber placement remains subjected to some limitations, due to the multiscale effect of laying tows and their manufacturing defects that could not be considered. Firstly, a simple model of cracks and strain energy is introduced in order to ensure that cracks' actual likelihood could be determined by using strain energy or density. An antisequential hierarchical multiscale collaborative optimization strategy is introduced to address the multiscale effect of structure and mechanical properties for laying tows or cracks in the high-speed fiber placement process. Multiscale mechanical properties of laying tow under various processing conditions are investigated by simulation, which includes recoverable strain energy of macroscale, mesh fiber/epoxy tow as an example.
Source link: https://doi.org/10.1155/2016/5480352
structural composites made by carbon fiber/epoxy laminates have been used in large aircraft industries for many years. The aim of this study was to reproduce thermal stress in the laminate plate created by temperature changes and monitoring potential cumulative damage on the laminate using ultrasonic C-scan inspection. The carbon fiber/epoxy plain weave laminate went from 60° to 80 °C, lasted for ten minutes, then repeated for 1000, 2000, 3000, and 4000 times. Only in specimens cycled 3000 times, or so, were found any changes in the laminate according to those who cycled 3000 times or so.
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