Toro, Paulo Gilberto de PaulaSolano, Alexander Alberto Camacho2024-04-022024-04-022023-12-18SOLANO, Alexander Alberto Camacho. Estudo conceitual aerodinâmico de um veículo scramjet para voo vertical em velocidade hipersônica constante na atmosfera terrestre densa. Orientador: Dr. Paulo Gilberto de Paula Toro. 2023. 88f. Dissertação (Mestrado em Engenharia e Ciências Aeroespaciais) - Escola de Ciências e Tecnologia, Universidade Federal do Rio Grande do Norte, Natal, 2023.https://repositorio.ufrn.br/handle/123456789/57985The concept of scramjet technology emerged in the 1950s as a solution to the speed limitations of its predecessor, ramjet engines. Almost 50 years after its conception, the first flight tests were carried out to prove the viability of this technology. Basically, a propulsion system based on scramjet technology is an aerospace vehicle that moves through the Earth's dense atmosphere at hypersonic speeds. This is possible by burning a mixture of air captured from the atmosphere and fuel (either hydrocarbon or hydrogen) at supersonic speed inside the combustion chamber. Currently, the most common way to access space is through launchers that use traditional propulsion systems, that is, solid propellant engines or liquid fuels. These vehicles require large structures due to the need to incorporate large tanks of solid propellants or fuel and oxidizer inside. These results in the creation of bulky structures that increase launch costs and consequently reduce payload capacity. At the Universidade Federal do Rio Grande do Norte (UFRN), since 2017, professors and students from different areas of engineering have worked together on aero-structural designs applied to scramjet technology. This research presents a conceptual study of a scramjet technology demonstrator designed for ascending flight at altitudes of 21 km, 26 km and 31 km, maintaining a constant hypersonic speed of 1.950 m/s in the Earth's dense atmosphere. The analytical theories of oblique shock wave, heat addition (Rayleigh) in a unidirectional flow in a cross section with constant area without addition of fuel mass, and the theory of area ratio were applied in compression sections, combustion chamber, and expansion, respectively. These theories were applied considering air as a perfect gas without the effects of high temperatures and without taking into account the viscous effects of the boundary layer. Initially, three vehicles were proposed, one for each altitude: 21 km, 26 km and 31 km. The compression section angles were determined to meet the supersonic speed (Mach number) and fuel ignition temperature (in this case, hydrogen), considering a stoichiometric mixture and spontaneous ignition. The compression section was optimized taking into account that all incident oblique shock waves have the same intensity, providing shock on-lip and shock on-corner conditions. The expansion section was optimized considering that the combustion products had the same pressure as the vehicle's flight altitude. Subsequently, the fixed geometry optimized for the altitude of 21 km was considered, taking into account the thermodynamic flight conditions at 26 km and 31 km. Similarly, the study of the optimized geometry was carried out at an altitude of 26 km in flight at altitudes of 21 km and 31 km, and the study of the optimized geometry at an altitude of 31 km in flight at altitudes of 21 km and 26 km. The results obtained from the demonstrator with fixed geometry at altitudes of 26 km and 31 km did not provide conditions for supersonic combustion to occur in the combustion chamber flying at lower altitudes. However, it was possible to find uninstalled thrust in two configurations: the study considering the design conditions with fixed geometries at flight altitudes of 21 km, 26 km or 31 km, and the study in the design condition with fixed geometry at an altitude of 21 km in flight at altitudes of 26 km or 31 km, of the same order of magnitude as the demonstrator under optimized design conditions at altitudes of 26 km or 31 km, respectively. Finally, the study indicates the possibility of atmospheric flight of the supersonic combustion demonstrator from altitudes of 21 km to 31 km, at a constant hypersonic speed of 1.950 m/s.Acesso AbertoScramjetCombustão supersônicaPropulsão hipersônica aspiradaAbordagem de engenhariamasterThesisCNPQ::ENGENHARIAS