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Submitted
August 1, 2023
Published
August 1, 2023
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Abstract

In this investigation, high velocity impact test was carried out to study the after effect of thermal loading on ballistic limits of composite laminates. Plain woven carbon/epoxy laminates with nominal thickness of 2.3 mm were fabricated by compression moulding technique. To study the effect of thermal loading, laminates were exposed to different temperatures of 60°C, 80°C, 100°C, 120°C, 140°C and 160°C for 24 h in hot air oven and brought back to room temperature. Impact test was carried out using single stage gas gun for velocity up to 115 m/s. The bullet used was Æ 9.6 mm and mass 14.20 gm. The results show that ballistic limit reduces from 83 m/s to 62 m/s with increase in loading temperature from 30°C to 160°C. For impact velocity above ballistic limit, energy absorbed by the laminates reduces with increase in loading temperature. Shear plug formation was observed during experiment as reported in literatures [4, 5 and 6]. An energy base mathematical model is employed to predict the ballistic limit. The model considered the energy loss due to various failure mechanisms that occurred during impact test. The predicted ballistic velocity and energy absorbed by laminates show good agreement with the experimental results.

Keywords

Carbon/epoxy composite; High velocity impact; Ballistic limit; Thermal loading.

Article Details

How to Cite
Velmurugan , R., & Barchha , S. (2023). Ballistic Performance of Thermally Exposed CFRP Composites. Journal of Aerospace Sciences and Technologies, 67(3), 396–407. https://doi.org/10.61653/joast.v67i3.2015.383
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