Metodologia para análise estrutural de envelopes-motor de foguetes de propulsão sólida desenvolvida pela AVIBRAS

• Autor(a) principal: Nagasaka, Caio Sadame [UNESP]
• Data de Publicação: 2015
• Tipo de documento: Trabalho de conclusão de curso
• Idioma: por
• Título da fonte: Repositório Institucional da UNESP
• Texto Completo: http://hdl.handle.net/11449/155382; http://www.athena.biblioteca.unesp.br/exlibris/bd/capelo/2017-05-02/000882539.pdf
• topic: Foguetes (Aeronáutica); Motores de foguetes; Vasos de pressão; Rockets (Aeronautics)

The rocket obtains moviment through ejection gases. Those gases come from the combustion of a solid propellant which are expanded and compressed through a nozzle. This process turns the intern pressure of combustion into a flow with supersonic velocity. Creating thrust, the force responsible for the moviment. In rocket motor design, the case should tolerate this internal pressure as the main stress agent. The typical motor case has one cylinder and two espheric domes at both ends, essencially it is a thin-walled pressure vessel. This work show a study metodology for determination of motor case wall thickness by calculating the combustion chamber internal pressure based on propulsives parameters of solid propellant. In addition, the restrictions of the applicability of this method