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<p>Re-entry space vehicles encounter intense aerothermal loads. To prevent the excessive heat from damaging the vehicle or its contents, a thermal protection system is essential. This study examines the effects of varying filler compositions on the thermal performance of four different composite materials: graphene–vinyl ester, graphene–epoxy, carbon nanotubes-vinyl ester, and carbon nanotubes-epoxy. Graphene and carbon nanotubes are used as fillers, with vinyl ester and epoxy serving as the resin matrices. The filler content in each composite is varied from 0.5 to 5% by weight, in increments of 0.5%. The main objective is to determine the Linear Ablation Rate (LAR) of these composites when subjected to thermal loads. Specific formulas are employed to calculate LAR for each composition. Results are displayed through graphs plotting LAR against distance (x, in mm) and against temperature (T, in Kelvin). These graphs provide insights into the thermal degradation behaviour and effectiveness of the composites. The findings aim to improve the understanding of the thermal protection capabilities of graphene and carbon nanotube-based composites, providing valuable data for their potential use in high-temperature environments.</p>

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Computational investigation on ablation kinetics of graphene and carbon nanotube reinforced thermoset polymeric composites

  • 期刊论文

  • 发表日期：

    2025年1月16日

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  • Karan Kumar,
  • Dhrub Narnolia,
  • Rahul Raj,
  • P. K. Jain,
  • Kaushik Kumar

摘要

Re-entry space vehicles encounter intense aerothermal loads. To prevent the excessive heat from damaging the vehicle or its contents, a thermal protection system is essential. This study examines the effects of varying filler compositions on the thermal performance of four different composite materials: graphene–vinyl ester, graphene–epoxy, carbon nanotubes-vinyl ester, and carbon nanotubes-epoxy. Graphene and carbon nanotubes are used as fillers, with vinyl ester and epoxy serving as the resin matrices. The filler content in each composite is varied from 0.5 to 5% by weight, in increments of 0.5%. The main objective is to determine the Linear Ablation Rate (LAR) of these composites when subjected to thermal loads. Specific formulas are employed to calculate LAR for each composition. Results are displayed through graphs plotting LAR against distance (x, in mm) and against temperature (T, in Kelvin). These graphs provide insights into the thermal degradation behaviour and effectiveness of the composites. The findings aim to improve the understanding of the thermal protection capabilities of graphene and carbon nanotube-based composites, providing valuable data for their potential use in high-temperature environments.