Modelling the tension and compression strengths of polymer laminates in fire

Mouritz, A, Mathys, Z and Gibson, A 2007, 'Modelling the tension and compression strengths of polymer laminates in fire', Composites Science and Technology, vol. 67, pp. 551-564.

Document type: Journal Article
Collection: Journal Articles

Title Modelling the tension and compression strengths of polymer laminates in fire
Author(s) Mouritz, A
Mathys, Z
Gibson, A
Year 2007
Journal name Composites Science and Technology
Volume number 67
Start page 551
End page 564
Total pages 14
Publisher Elsevier Science
Abstract Thermo-mechanical models are presented for predicting the time-to-failure of polymer laminates loaded in tension or compression and exposed to one-sided radiant heating by fire. Time-to-failure is defined as the time duration that a polymer laminate can support an externally applied load in a fire without failing. The models predict the temperature rise and through-thickness temperature profile in a hot decomposing laminate exposed to fire. Using this thermal data, mechanics-based models based on residual strength analysis are used to calculate the time-to-failure. A preliminary evaluation of the accuracy of the models is presented using failure times measured in fire-under-load tests on a woven glass/vinyl ester laminate. The model was evaluated at temperatures between -250 and 800 ºC by testing the laminate at heat flux levels between 10 and 75 kW/m2. It was found that the time-to-failure of the laminate decreased with increasing heat flux and increasing applied stress for both the compression and tension load conditions. The tests also revealed that the failure times were much shorter (by about one order of magnitude) when the laminate was loaded in compression. The models can predict the time-to-failure with good accuracy for both compression and tension loading for certain heat flux levels. However, because the models have only been evaluated for one type of laminate (woven glass/vinyl ester), further evaluation is necessary for other laminate systems. The paper also presents new experimental insights into the strengthening mechanisms of laminates at high temperature.
Subject Aerospace Materials
Keyword(s) Composite Panels
Thermal Response
DOI - identifier 10.1016/j.compscitech.2006.07.038
ISSN 0266-3538
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Citation counts: TR Web of Science Citation Count  Cited 96 times in Thomson Reuters Web of Science Article | Citations
Scopus Citation Count Cited 95 times in Scopus Article | Citations
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