Abstract
A Thermal Protection System (TPS) protects the vehicle from the extreme heat generated during high-speed flow. The heat-shield used for thermal protection adds significant weight to the vehicle, which is undesirable. There has been little info available in the open literature about the thermal analysis of a heat-shield coupled with fluid flow and its weight optimization. Moreover, the current understanding of such research still contains uncertainties. This paper presents the thermal analysis and optimization of a blunt nose semi-spherical heat-shield in hypersonic flow at Mach 7.99. A high-order shock-fitting algorithm that solves the hypersonic flow is used to compute the heat flux at the outer surface of the heat-shield. Based on the surface heat flux computed using the fluid solver, a transient conduction equation is solved to predict the temperature distribution in the heat-shield and the inner cabin temperature. The heat-shield thickness optimization is done based on the inner cabin temperature using the Newton-Raphson method, which reduces the overall weight of the heat-shield.
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Kumar, C., Prakash, A. (2023). Optimization of Blunt Nose Semi-spherical Heat-Shield in Hypersonic Flow at Mach 7.99. In: Pradeep Pratapa, P., Saravana Kumar, G., Ramu, P., Amit, R.K. (eds) Advances in Multidisciplinary Analysis and Optimization. NCMDAO 2021. Lecture Notes in Mechanical Engineering. Springer, Singapore. https://doi.org/10.1007/978-981-19-3938-9_1
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DOI: https://doi.org/10.1007/978-981-19-3938-9_1
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