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Impact of Carbon Nanotubes on the Mechanical and Electrical Properties of Silicone

Sałaciński Michał, Dydek Kamil, Leski Andrzej, Kozera Rafał, Mucha Mateusz, Karczmarz Wojciech

Fatigue of Aircraft Structures

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2022

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Iss. 14

135--153

EN

This paper presents the results of a structure study of a dispersion composite on a silicone matrix with a filler in the form of multi-walled carbon nanotubes (MWCNTs). The study aims to determine the effect of the filler on the composite mechanical properties and electrical conductivity. Materials that are electrically conductive and exhibit high mechanical properties can find applications in high-strain sensors. During the study, the characteristic properties of the susceptible materials, silicone alone and silicone with different filler contents (4%, 6%, and 8% by weight), were determined after curing. Microscopic observations were performed to assess the influence of carbon fillers on the material structure and to determine the level of homogeneity of the material. Examination of mechanical properties facilitated the determination of the Shor A hardness (ShA), stiffness, and Poisson’s ratio of the cured composites, depending on the nanotubes’ content. In parallel with the study of mechanical properties, the effect of loading, and the associated deformation of the samples, on the conductivity of the composite was investigated. Based on the results obtained, a discussion was carried out on the type of conductivity characteristic of silicone with different filler content as well as depending on the level of deformation of the samples.

2

Selected Construction Properties of Hybrid Epoxy Composites Reinforced with Carbon Fiber and Alumina

Krzyżak Aneta, Relich Szymon, Kosicka Ewelina, Szczepaniak Robert, Mucha Mateusz

Advances in Science and Technology. Research Journal

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2022

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Vol. 16, no 2

240--248

EN

The purpose of this study is to investigate the impact of the introduction of powder modifier into composite reinforced with carbon fabric on selected mechanical properties. The tests were performed on 16 groups of hybrid epoxy composites, including one reference group and 15 groups containing alumina with the grain size of F220, F240, F280, F320 and F360, added in the weight percent of 5%, 10% and 15%. This composite was made of certified components designed for application in the aviation industry. Test results indicated that an increase of alumina content by weight caused a decrease of strength of polymer composites in most tests. In addition, the value of the force transferred by the composite in the tensile test increased disproportionately to the cross section, which resulted in decreased strength, while the addition of alumina impeded the super-saturation of the carbon fabric, which caused discontinuities in the matrix material.

3

The effect of the heat treatment on the crosslinking of epoxy resin for aviation applications

Mucha Mateusz, Sterzyński Tomasz, Krzyżak Aneta

Polimery

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2020

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T. 65, nr 11-12

776--783

EN

We have investigated the MGS L285 epoxy laminating resin system, used in aviation applications. A number of tests were carried out, namely Dynamic Mechanical Analysis (DMA), Differential Scanning Calorimetry (DSC), tensile testing, three-point bending flexural testing, Charpy impact testing, Shore D hardness, density measurements and Fourier-Transform Infrared spectroscopy (FT-IR). Moreover, the tensile toughness UTT, the brittleness B and the linear isobaric thermal expansivity αL were calculated. The samples were subjected to heat treatment in the temperatures of 50, 60 and 80°C for 15 hours or were stored in room temperature. Glass transition temperature, hardness, density as well as other properties were observed to rise along with the increasing heat treatment temperature, suggesting the validity of applications of Voronoi-Delaunay structural analysis to polymer science. On the other hand, properties such as brittleness, toughness and impact strength exhibited a non-linear course of changes as a function of the heating temperature.

PL

Badano laminującą żywicę epoksydową MGS L285 przeznaczoną do zastosowań w lotnictwie. Przeprowadzono dynamiczną analizę mechaniczną (DMA), skaningową kalorymetrię różnicową (DSC), statyczną próbę rozciągania, zginanie trójpunktowe, badanie młotem Charpy’ego, pomiary twardości metodą Shore’a D, pomiary gęstości, zarejestrowano także widma metodą skaningowej spektroskopii transformatorowej Fouriera (FT-IR). Obliczono wartości wiązkości UTT, kruchości B i izobarycznej rozszerzalności termicznej αL. Próbki wygrzewano w temperaturze 50, 60 lub 80 stopni Celsjusza przez 15 h lub przechowywano w temperaturze pokojowej. W odniesieniu do dużej części badanych właściwości zaobserwowano ich poprawę wraz z rosnącą temperaturą wygrzewania. Korelacja temperatury zeszklenia, twardości i gęstości polimerów wskazuje na słuszność zastosowania w badaniu wolnych objętości analizy strukturalnej opartej na triangulacji Delone i diagramach Woronoja. W wypadku właściwości, takich jak: kruchość, wiązkość i udarność stwierdzono nieliniowy przebieg zmian w funkcji temperatury wygrzewania.