Projeto de motor foguete classe M e redutor de pressão para a medição da pressão interna em motor foguete a combustível sólido classe M para missões com 2 km de apogeu

Abstract

Due to the large number of variables involved in the propulsion process of a rocket, proper instrumentation is required. Pressure and thrust are important parameters for understanding the behavior and performance of the propulsion system and propellants. This work aims to design a class M rocket motor, validated for a mission apogee of 2 kilometers through flight simulations using OpenRocket software. Followed by the objective of dimensioning a pressure reducer that enables the reading of the internal pressure in the combustion chamber of Class M solid propellant rocket motors, as well as the generated thrust, through instrumentation on static test benches. The work presents a structural analysis of the motor components to ensure safe operation and preservation of the instruments during the measurement. The analyzes were validated through a simulation in SolidWorks software using the finite element method. The system will later be manufactured and implemented by the Potiguar Rocket Design team.