Synthesis and Analysis of Ultra-High Temperature Ceramic Intended for Aerospace Applications

Abstract

Aerodynamic drag and heat are crucial in the thermal stability of hypersonic space shuttle at different speeds. The latest developments in the design of space shuttle wing structure require an effective Thermal Protection System (TPS) that will meet the need of space research technology. In this research a typical space shuttle wing with different Ultra High Temperature ceramic (UHTC) composite TPS materials like alumina refectories Al2O3(48 to 58%) with addition of Silicon dioxide (SiO2), Titania (TiO2), Iron Oxide (Fe2O3), Calcium oxide (CaO) is analyzed and compared for its effective protection against transfer of heat in to the structure. A model of the wing is designed and analyzed by commercial software. Quad 4 node elements were adopted to perform coupled thermal and structural analysis in ANSYS 18.2 software. From the numerical analysis single composition was finalized and synthesized by hot pressing. Properties like density, hardness, compressive strength and temperature stability were evaluated. The compressive strength was found 16.75 MPa and hardness 83.2 HRB which is more than the HRSI tiles.