الفهرس 
English Cover
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Abstract
Aircraft carbon {uFB01}ber/epoxy composite material is sensitive to lightning strike. Its damage and protection design suffering from lightning strike is becoming increasingly important. A numerical model is proposed to describe an arc and its interaction with a composite material in an anodic con{uFB01}guration. After a validation step with published experimental results in two dimensions (2D), the model is used to quantify the degradation level of the material versus the pulse duration and the current intensity value. A three-dimensional (3D) model is then developed and used to evaluate the degradation of the composite material. This model shows the behaviour of the plasma column representing the lightning strike and quanti{uFB01}es the power transferred to the anode.The contribution of this study is modeling the composite panels{u2019} material properties as temperature dependent, which was excluded by other researchers. The order of estimated temperature (of the order of 45,000 K) and pressure (of the order of 0.1-0.2 MPa) suggests that the waveform {u2013} C damage is mainly due to thermoelectric effect, while pressure effect is minimum