Leonardo Vieira Cunha

Abstract

While operating, rocket parts that serve as escape valves for the combustion gases are subject to high temperatures. Through the use of the Finite Elements Method, this work proposes a study of the temperature distribution inside an operating minirocket’s nozzle, via the development of one’s own platform for thermal studies, in threedimensional, transient state, and for complex and varied geometries, utilizing linear tetrahedral elements for spacial discretization. Script verifications have also been performed, comparing the numerical results with analytical ones. Finally, the temperature on the inside walls of a minirocket’s nozzle have been found

Advising

Advisor: Anjos, G. R.