MODELLING AND ANALYSIS OF ALLOY MATRIX MATERIAL AS CONSIDERED FOR ROCKET BODY

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. High temperature withstand materials have to produce for space applications to resist different atmospheric conditions to overcome. At different stages of orthogonal momentum there is a possibility of temperature variation and external stresses on front part of rocket. Even though many applications developed for durability of rockets still there is a need of analyzing the application with different matrix alloys. In the present paper we are modelling and analyzing the rocket structure by giving alloy matrix material mix with Ni, and TiB2 whose liquefaction temperature is high. The project modelled in CREO 3.0 and the thermal analysis carried out in ANSYS work bench 15.0. The results obtained compared with the before researches to get optimal results for further combinations.