Abstract
Spacecraft needs thermal protection systems material that rise more than ±1.260 °C on nose cap and wing leading edge. It depends on the heat loading encountered during the re-entry of the orbiter into the atmosphere. Recently, the spacecraft uses thermal protection system (TPS) materials like reinforced carbon-carbon (RCC), High-Temperature Reusable Surface Insulation (HRSI), Low-Temperature Reusable Surface Insulation (LRSI), and Felt Reusable Surface Insulation (FRSI). The TPS is an isolator material which have range temperature −121 °C until 1.649 °C. This paper analyzes Tantalum Carbide (TaC) and Hafnium Carbide (HfC) for spacecraft material. We show that Tantalum Carbide (TaC) and Hafnium Carbide (HfC) would rise above the TPS materials temperature. The comparison among RCC, HRSI, LRSI, FRSI, and TaC-HfC is on the heat resistant temperature. The TaC and HfC is heat resistant material that rise 3726.85 °C. The TaC-HfC is recommended for spacecraft using, especially on nose cap and lower surface. Nose cap and lower surface are area of spacecraft body which would experience extremely high temperatures when aircraft fly to left and entry the atmosphere.
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This work is supported by Indonesia Defense University.
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Aritonang, S., Ezha Kurniasari, W.S., Juhana, R., Herawan, T. (2021). Analyzing Tantalum Carbide (TaC) and Hafnium Carbide (HfC) for Spacecraft Material. In: Osman Zahid, M.N., Abdul Sani, A.S., Mohamad Yasin, M.R., Ismail, Z., Che Lah, N.A., Mohd Turan, F. (eds) Recent Trends in Manufacturing and Materials Towards Industry 4.0. Lecture Notes in Mechanical Engineering. Springer, Singapore. https://doi.org/10.1007/978-981-15-9505-9_81
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