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

Millen, Scott; Kumar, Vipin; Murphy, Adrian

doi:10.4271/01-16-02-0017

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

Journal Article · 27 April 2023 · SAE International Journal of Aerospace

DOI: https://doi.org/10.4271/01-16-02-0017 · OSTI ID:1973327

Millen, Scott ^[1];

^[2]; Murphy, Adrian ^[1]

Queen's Univ., Belfast, Northern Ireland (United Kingdom)
Oak Ridge National Laboratory (ORNL), Oak Ridge, TN (United States)

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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Research Organization:: Oak Ridge National Laboratory (ORNL), Oak Ridge, TN (United States)

Sponsoring Organization:: USDOE Office of Energy Efficiency and Renewable Energy (EERE)

Grant/Contract Number:: AC05-00OR22725

OSTI ID:: 1973327

Journal Information:: SAE International Journal of Aerospace, Journal Name: SAE International Journal of Aerospace Journal Issue: 2 Vol. 16; ISSN 1946-3855

Publisher:: SAE MobilusCopyright Statement

Country of Publication:: United States

Language:: English

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36 MATERIALS SCIENCE
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