Projeto conceitual de um scramjet para inserção de cubesat em órbita, empregando uma abordagem analítica

• Ano de defesa: 2022
• Autor(a) principal: Pereira, Marcos Vinicius Sabino
• Tipo de documento: Dissertação
• Tipo de acesso: Acesso aberto
• Idioma: por
• Instituição de defesa: Universidade Federal do Rio Grande do Norte; Brasil; UFRN; PROGRAMA DE PÓS-GRADUAÇÃO EM ENGENHARIA AEROESPACIAL
• Palavras-chave em Português: Scramjet; Combustão supersônica; Propulsão hipersônica aspirada; Estudo analítico; CubeSat
• Link de acesso: https://repositorio.ufrn.br/handle/123456789/47669

In order to access the space through the application of hypersonic airbreathing propulsion technology, this work presents the development scramjet (supersonic combustion ramjet). The aerospace vehicle proposed in this work will have three stages, two stages of rocket engines with solid propulsion and a stage composed by a scramjet with four combustion chambers. The scramjet of this vehicle will operate in vertical flight in the Earth’s atmosphere, from 20 km to 60 km of altitude with hypersonic speed of 1710 m/s, corresponding to approximately Mach number 5.8. Bearing in mind that the scramjet has no moving parts and needs a system that accelerates it, up to supersonic combustion conditions, it will be necessary to use the accelerator vehicle that is responsible for propelling the scramjet to the ideal operating conditions (Mach number, position, dynamic pressure). This aerospace vehicle will have the utility of accessing space and conducting drilling experiments, insertion of CubeSat into orbit and training the specialized labor responsible for aerospace operations. For the development of this work, it is necessary to use the theories referring to the formation of shock waves and expansion waves, in addition to the theories related to the addition of heat and the formation of a boundary layer in flow with hypersonic velocity. The preliminary results of this work indicate that the scramjet will be able to generate thrust and that when considering the existence of the boundary layer, a change in the geometry of the vehicle's inlet is necessary, so that it is possible to maintain the formation of shock on-lip and shock on-corner in the scramjet structure.