Estudos sobre o uso de um motor scramjet como estágio atmosférico em um veículo lançador de nanossatélites

• Ano de defesa: 2022
• Autor(a) principal: Silva, Elder Samuel Taveira da
• 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; Veículo lançador; Nanossatélites
• Link de acesso: https://repositorio.ufrn.br/handle/123456789/47668

This Master Degree thesis presents a preliminary design of an aerospace vehicle, using hypersonic airbreathing propulsion based on supersonic combustion (scramjet technology), for atmospheric flight at 20 km altitude, at hypersonic speed, corresponding to Mach number 5.79. Scramjet is an aeronautical engine without moving parts, where the aerospace vehicle integrated with scramjet technology (propulsion system) must be coupled to a rocket engine. The current means of access to space is limited by the chemical propulsion system (solid and / or liquid fuel) carried onboard rockets. The technology of supersonic combustion (scramjet) is being studied as an airbreathing propulsion system, to be used in the dense layers of the Earth's atmosphere, to access space. A demonstrator was being designed to be coupled to the Sonda III rocket engine, to operate as a second stage, starting the operation at 20 km altitude. The theory of oblique shock waves, the theory of heat addition in one-dimensional flow (Rayleigh's theory) and the theory of expansion waves (by Prandtl-Meyer) coupled to the area ratio are applied in the design of the compression sections, of combustion and expansion, respectively, of the scramjet demonstrator with internal admission configuration. Steady state, onedimensional flow and air under calorically perfect gas conditions are considered. Thermodynamic properties (pressure, temperature, density, speed of sound) and flow velocity (Mach number) is presented along the streamline from the leading edge to the trailing edge of the demonstrator, considering flow without and with boundary layer effects, for the conditions of no fuel burning (power-off) and fuel burning (power-on). Finally, the conceptual design and a brief approach to systems engineering in the development of a nanosatellite launch vehicle are presented.