TY - GEN
T1 - Simulation of lightning-strike-induced thermal ablation in unprotected carbon fiber polymer matrix composite laminates
AU - Wang, Yeqing
AU - Zhupanska, Olesya I.
AU - Pasiliao, Crystal
N1 - Publisher Copyright:
Copyright © 2016 by ASME.
PY - 2016
Y1 - 2016
N2 - In this work, the influence of lightning-strike-induced electric current and surface heat flux on the thermal response and thermal ablation of a carbon fiber polymer matrix composite laminated panel is studied. A coupled electricthermal model for an anisotropic plate exposed to the lightningstrike-induced electric current and surface heat flux is formulated. Temperature-dependent material properties of the carbon fiber polymer matrix composites, including electrical conductivity, thermal conductivity, and specific heat, are used. A coupled electric-thermal finite element analysis (FEA) is conducted using a MATLAB-ABAQUS integrated numerical procedure, which enables progressive element deletion to accurately model the lightning-strike-induced continuous surface recession (thermal ablation) in the composite panel. The obtained thermal response and thermal ablation using the proposed numerical procedure are compared with those obtained using existing solution procedures without progressive element deletion.
AB - In this work, the influence of lightning-strike-induced electric current and surface heat flux on the thermal response and thermal ablation of a carbon fiber polymer matrix composite laminated panel is studied. A coupled electricthermal model for an anisotropic plate exposed to the lightningstrike-induced electric current and surface heat flux is formulated. Temperature-dependent material properties of the carbon fiber polymer matrix composites, including electrical conductivity, thermal conductivity, and specific heat, are used. A coupled electric-thermal finite element analysis (FEA) is conducted using a MATLAB-ABAQUS integrated numerical procedure, which enables progressive element deletion to accurately model the lightning-strike-induced continuous surface recession (thermal ablation) in the composite panel. The obtained thermal response and thermal ablation using the proposed numerical procedure are compared with those obtained using existing solution procedures without progressive element deletion.
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U2 - 10.1115/IMECE201665728
DO - 10.1115/IMECE201665728
M3 - Conference contribution
AN - SCOPUS:85021673280
T3 - ASME International Mechanical Engineering Congress and Exposition, Proceedings (IMECE)
BT - Advances in Aerospace Technology
PB - American Society of Mechanical Engineers (ASME)
T2 - ASME 2016 International Mechanical Engineering Congress and Exposition, IMECE 2016
Y2 - 11 November 2016 through 17 November 2016
ER -