The Influence of Carbon Fiber Composite Specimen Design Parameters on Artificial Lightning Strike Current Dissipation and Material Thermal Damage

Scott Millen, Vipin Kumar, Adrian Murphy

Research output: Contribution to journalArticlepeer-review

5 Scopus citations

Abstract

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.

Original languageEnglish
Pages (from-to)231-246
Number of pages16
JournalSAE International Journal of Aerospace
Volume16
Issue number2
DOIs
StatePublished - Apr 29 2023

Funding

Vipin Kumar was supported by the US Department of Energy, Office of Energy Efficiency and Renewable Energy, Advanced Manufacturing Office, under contract DE-AC05-00OR22725 with UT-Battelle, LLC.

FundersFunder number
U.S. Department of Energy
Advanced Manufacturing OfficeDE-AC05-00OR22725
Office of Energy Efficiency and Renewable Energy

    Keywords

    • Aerospace materials
    • Carbon fiber
    • Composite damage
    • Computational modelling
    • Current dissipation
    • Finite element analysis (FEA)
    • Lightning strike

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