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Research Article Open Access
Aerodynamic drag and heating are the crucial in the thermal stability of hypersonic vehicles at various speeds. The latest developments in the design of nose cone structure demands an effective Thermal Protection System (TPS) meets the need of the space research technology. In this research a typical nose cone with different Ultra High Temperature (UHT) ceramic composite TPS materials like Hafnium diboride (HfB2) and zirconium diboride (ZrB2) is analyzed and compared for its effective protection against transfer of heat into the structure. A naval model is designed for from the concepts of blunt nose cone and analyzed with the commercial software. A typical quad 4 node element is adopted to perform thermal analysis in ANSYS software and the simulated results are validated with numerical solutions. Existing ablative materials like SLA-561V, SIRCA and AVCOAT are having the heat flux ranges up to 110 W/cm2 and temperatures ranging up to 2000ÃÂC and need of new materials and its reliability are focused in this research.
Thermal Protection System, Thermal stability, blunt nose cone, UHT ceramic Composite., Aerospace Engineering,Applied Electronics,Applied Sciences,Biochemistry,Biogenetic Engineering,Chromatography Techniques.