Fire Burnthrough Response of CFRP Aerostructures. Numerical Investigation and Experimental Verification

被引：12

作者：

Sikoutris, Dimitris E. ^{[1
]}

Vlachos, Dimitris E. ^{[1
]}

Kostopoulos, Vassilis ^{[1
]}

Jagger, Stuart ^{[2
]}

Ledin, Stefan ^{[2
]}

机构：

[1] Univ Patras, Appl Mech Lab, Dept Mech Engn & Aeronaut, GR-26500 Patras, Greece

[2] HSL, Hlth & Safety Lab, Buxton SK17 9JN, Derby, England

来源：

APPLIED COMPOSITE MATERIALS | 2012年 / 19卷 / 02期

关键词：

Carbon fiber composites; High-temperature properties; Thermal properties; Progressive CFRP fire-degradation; Finite element analysis (FEA); Fire burnthrough modeling;

D O I：

10.1007/s10443-011-9187-x

中图分类号：

TB33 [复合材料];

学科分类号：

摘要：

Aircraft structures are designed to withstand further to dynamic mechanical loadings thermal loads too. In the event of an external fire (while the aircraft is on the ground) the fuselage structure has to withstand and delay fire penetration. Prolonged burnthrough time is the design target. In the current work, a progressive fire-degradation material model is developed that links decomposition kinetics with the thermophysical properties of polymer composite materials. The material model is then implemented in a FE model to simulate the response of the flat panels under fire burnthrough conditions. Experimental investigation is performed in accordance to the ISO2685:1998 (E) Standard.

引用

页码：141 / 159

页数：19