THERMAL ANALYSIS OF THE BRAZILIAN 14-X HYPERSONIC AEROSPACE VEHICLE AT MACH NUMBER 7
Felipe Jean da Costa1; Israel da Silveira Rêgo2; Marco Antônio Sala Minucci2; Paulo Gilberto de Paula Toro2
1 ITA - Instituto Tecnológico de Aeronáutica; 2 IEAv - Instituto de Estudos Avançados
doi:10.20906/CPS/CON-2016-1216
Resumo
The Brazilian 14-X Hypersonic Aerospace Vehicle, designed at the Prof. Henry T. Nagamatsu Laboratory of Aerothermodynamics and Hypersonics, at the Institute for Advanced Studies, is a technological demonstrator endowed with two innovative technologies: waverider technology, to obtain lift from conical shockwave during the hypersonic flight; and hypersonic airbreathing propulsion system based on supersonic combustion (scramjet), to fly at Earth's atmosphere at 30 km altitude at Mach numbers 7 and 10. Basically, scramjet is an aeronautical engine without moving parts that uses the conical/oblique shock waves generated during the hypersonic flight, to promote compression and deceleration of freestream atmospheric air at the inlet of the scramjet. On the understanding of the aerodynamic heating it is important to analyze the heat conduction transfer to the 14-X waverider internal structure. ANSYS Workbench software provides the Thermal Numerical Analysis, using Finite Element Method of the 14-X waverider unpowered scramjet at 30 km altitude at Mach number 7 and 10 in terms of temperature and heat flux. Finally, it's possible to verify if the internal temperature comply with the requirements for embedded systems, and, if is necessary to do modifications on the structure in terms of wall thickness and materials.
Palavras-chave: scramjet; 14-X; Hypersonics; Thermal Analisys; Finite Element Method