The analysis of the properties of ablative composites with carbon and MMT nanofiller reinforcement

• Autorzy: Szczepaniak R. , Czubak K. , Przybyłek P. , Stabryn S.

Identyfikatory

DOI

10.5604/01.3001.0010.3153

• Języki publikacji: EN

Abstrakty

EN

One of the most important parameters in the selection of composite materials used for the protection of avionics instruments exposed to high temperatures are ablative properties. They constitute the main criterion in determining the composition and thickness of the protective material. In this article, the authors determine the ablative properties of a polymer matrix with carbon reinforcement and check the effect of using the MMT additive (montmorillonite) on the change in the resistance to the impact of a high heat flux. The tested materials play an important role in the defence, aviation and space industry. Ablative materials are the only ones to protect the rear wall surface from an excessive temperature rise while using a thin insulation wall. For the sake of the research, we prepared a series of samples of the composite produced with epoxy resin LH 145, H 147 hardener, carbon fibre mats and the addition of MMT. The prepared samples were tested on a unique stand in laboratory conditions. The findings obtained from the experimental testing after a detailed analysis were tabulated and presented in the form of graphs. The authors determined the ablative loss of mass of the individual samples, compared their internal temperatures, which had been measured with thermocouples, as well as the temperature on the backside of the sample. In addition, in order to complement the experimental studies of determining the temperature rise on the rear surface, the authors used a thermal imaging camera. Besides, they took photos of different layers of the examined structure, which had been exposed, to a heat stream, by means of a scanning microscope.

Słowa kluczowe

EN

composite; ablative properties; nanotube; carbon fibre; ablation

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2017
• Tom: Vol. 24, No. 4
• Strony: 305--312
• Opis fizyczny: Bibliogr. 18 poz., rys.

Twórcy

autor

Szczepaniak R.

• Polish Air Force Academy, Aeronautics Faculty Dywizjonu 303 Street 25, 08-521 Deblin, Poland tel.: + 48 261 517 427, 48 261 517 429

autor

Czubak K.

• Polish Air Force Academy, Aeronautics Faculty Dywizjonu 303 Street 25, 08-521 Deblin, Poland tel.: + 48 261 517 427, 48 261 517 429

autor

Przybyłek P.

• Polish Air Force Academy, Aeronautics Faculty Dywizjonu 303 Street 25, 08-521 Deblin, Poland tel.: + 48 261 517 427, 48 261 517 429

autor

Stabryn S.

• Polish Air Force Academy, Aeronautics Faculty Dywizjonu 303 Street 25, 08-521 Deblin, Poland tel.: + 48 261 517 427, 48 261 517 429

Bibliografia

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• [15] Reis P. N. B., Ferreira J. A. M., Zhang Z. Y., Benameur T., Richardson M. O. W., Compo-sites Part B, 46, pp.7-14, 2013.
• [16] Zhang, J., Chaisombat, K., He, S., Wang, C. H., Hybrid composite laminates reinforced with glass/carbon woven fabrics for lightweight load bearing structures, Materials and Design, vol. 33, pp. 75-80, 2012.
• [17] Zhang, Z., Thermo-Mechanical Behavior of Polymer Composites Exposed to Fire, PhD thesis, Blacksburg, Virginia 2010.
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Uwagi

PL

Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę (zadania 2017).