Abstract
This article focus on the study of Transition or Back wall Temperature behavior in PAN based composite materials with and without Silicon Carbide filler was investigated. PAN fabric is one of the most useful reinforcement materials in the composites, its major use being the manufacture of components in aerospace, automotive and missile technology. In this study, PAN carbon fabric laminates were prepared by Hand lay-up technique with and without Silicon Carbide filler. The experimental work was done on studying the Transition or Back wall Temperature characterization and ablative studies through Oxy-acetylene testing. The study results revealed that it exhibits the better thermal protection shield in PAN based Silicon Carbide filler laminate compared without adding filler material. However, the ablation rate study results were exhibits better erosion rate of CP laminate with Sic filler for thermal insulation.
Highlights
In aerospace application the re-entry vehicle structures are generally made of a structural member and thermal protection member made by the combination of Carbon/ Epoxy (CE) and over above Carbon/Phenolic (CP)
The comparative study has been carried out between the two laminates designated as Carbon Phenolic laminate without filler and Carbon Phenolic laminate with Silicon carbide filler
The investigation revealed that Carbon Phenolic laminate with Silicon carbide filler exhibits the better transition temperature compared without adding the Silicon Carbide (Sic) filler material
Summary
In aerospace application the re-entry vehicle structures are generally made of a structural member and thermal protection member made by the combination of Carbon/ Epoxy (CE) and over above Carbon/Phenolic (CP). For optimum performance of electronic packages mounted inside the CE + CP shell, the temperature inside the shell should be ideally be less than 100°C. The major objective of this study the back wall temperature of Carbon-Phenolic laminate with and without Silicon Carbide filler laminates. The study of back wall temperature represents an understanding of that material which was selected when subjected to high temperature under a specific time period, what would be its back wall temperature so as to assess its suitability for its intended use. Since, advanced composite materials are very widely used in aerospace applications because of its exotic properties. The final materials would be able to form complex shapes and should be as light as possible
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