碳纤维复合材料试样设计参数对人工雷击电流耗散和材料热损伤的影响

IF 0.3 Q4 ENGINEERING, AEROSPACE
Scott L J Millen, Vipin Kumar, A. Murphy
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引用次数: 1

摘要

先前的人工雷击直接效应研究已经检验了广泛的样本设计参数。没有研究过这种试样设计参数和电边界条件如何影响通过单个层的电流耗散。本文评估了碳纤维复合材料试样设计参数(设计参数=试样尺寸、形状和堆叠顺序)和电边界条件对焦耳加热引起的电流耗散和损伤扩散的影响。使用热电有限元(FE)建模,并生成实验室规模(1m长)模型,其中预测了层压板电流耗散,考虑到固定的人工雷电电流波形。模拟结果建立了从给定帘布层离开试样的电流与该帘布层中的热损伤量之间的正相关性。结果还表明,从撞击位置到零电位边界条件(地面)的离地距离是决定每个层中电流耗散的控制因素。值得注意的是,与地面的距离取决于每个样本的形状、尺寸、堆叠顺序和地面边界条件的位置。因此,不可能将电流耗散和损伤与试样设计和边界条件设置解耦。然而,可以为给定的试样形状、堆叠顺序和波形定义试样尺寸,以限制试样尺寸对所产生的电流分布和损伤的影响。对于多次出现在文献中的矩形试样设计,如100×150 mm,堆叠顺序为[45/0/−45/90]4s,需要大于300×200 mm的试样设计,以限制试样尺寸对电流分布和损伤的影响。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
The Influence of Carbon Fiber Composite Specimen Design Parameters on Artificial Lightning Strike Current Dissipation and Material Thermal Damage
Previous artificial lightning strike direct effect research has examined a broad range of specimen design parameters. No works have studied how such specimen design parameters and electrical boundary conditions impact the dissipation of electric current flow through individual plies. This article assesses the influence of carbon fiber composite specimen design parameters (design parameters = specimen size, shape, and stacking sequence) and electrical boundary conditions on the dissipation of current and the spread of damage resulting from Joule heating. Thermal-electric finite element (FE) modelling is used and laboratory scale (<1 m long) and aircraft scale (>1 m long) models are generated in which laminated ply current dissipation is predicted, considering a fixed artificial lightning current waveform. The simulation results establish a positive correlation between the current exiting the specimen from a given ply and the amount of thermal damage in that ply. The results also establish that the distance to ground, from the strike location to the zero potential boundary conditions (ground), is the controlling factor which dictates the electric current dissipation in each ply. Significantly, this distance to ground is dependent on each of the specimen shape, dimensions, stacking sequence, and location of ground boundary conditions. Therefore, it is not possible to decouple current dissipation and damage from specimen design and boundary condition setup. However, it is possible to define a specimen size for a given specimen shape, stacking sequence, and waveform which limit the influence of specimen dimensions on the resulting current distribution and damage. For a rectangular specimen design which appears in literature multiple times, as 100 × 150 mm and with a stacking sequence of [45/0/−45/90]4s, a specimen design of greater than 300 × 200 mm is required to limit the influence of specimen dimensions on current distribution and damage.
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来源期刊
SAE International Journal of Aerospace
SAE International Journal of Aerospace ENGINEERING, AEROSPACE-
CiteScore
0.70
自引率
0.00%
发文量
22
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