TY - GEN
T1 - Thermal ablation in fiber-reinforced composite laminates subjected to continuing lightning current
AU - Wang, Yeqing
AU - Zhupanska, Olesya I.
N1 - Publisher Copyright:
© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2016
Y1 - 2016
N2 - This work is concerned with thermal ablation modeling in carbon fiber-reinforced polymer-matrix composite laminates subjected to the lightnig strike. Both direct heat injection and Joule heating produced by the lightning current are taken into account. First, a model describing interaction of the lightning current channel with a conductive structure is presented. The model includes channel expansion and spatial and temporal distribution of the lightning current and linghtning-induced heat flux. Second, anisotropic electrical and thermal properties of the CFRP composite laminates are determined in a wide temperature range (up to the sublimation temperature of the carbon fibers) using experimental data and micromechanics considerations. Third, a nonlinear thermo-electric coupled problem is formulated and solved for a CFRP composite laminate to determine the electric-current-induced temperature distribution and associated thermal ablation. Finally, the obtained predictions of thermal ablation in the CFRP composite laminate are compared to the reported experimental results. It is found that the predicted thermal ablation depths agree well with those reported in the experimental study.
AB - This work is concerned with thermal ablation modeling in carbon fiber-reinforced polymer-matrix composite laminates subjected to the lightnig strike. Both direct heat injection and Joule heating produced by the lightning current are taken into account. First, a model describing interaction of the lightning current channel with a conductive structure is presented. The model includes channel expansion and spatial and temporal distribution of the lightning current and linghtning-induced heat flux. Second, anisotropic electrical and thermal properties of the CFRP composite laminates are determined in a wide temperature range (up to the sublimation temperature of the carbon fibers) using experimental data and micromechanics considerations. Third, a nonlinear thermo-electric coupled problem is formulated and solved for a CFRP composite laminate to determine the electric-current-induced temperature distribution and associated thermal ablation. Finally, the obtained predictions of thermal ablation in the CFRP composite laminate are compared to the reported experimental results. It is found that the predicted thermal ablation depths agree well with those reported in the experimental study.
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U2 - 10.2514/6.2016-0986
DO - 10.2514/6.2016-0986
M3 - Conference contribution
AN - SCOPUS:85088063854
SN - 9781624103926
T3 - 57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
BT - 57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2016
Y2 - 4 January 2016 through 8 January 2016
ER -