Eventos Anais de eventos
COBEM 2021
26th International Congress of Mechanical Engineering
PASSIVE THERMAL PROTECTION MATERIALS FOR HYPERSONIC AIRBREATHING FLIGHT VEHICLES
Submission Author:
Raysa Cristiano Paulino Pereira , RN
Co-Authors:
Raysa Cristiano Paulino Pereira, George Marinho, Paulo Toro, Rubens Maribondo do nascimento
Presenter: Raysa Cristiano Paulino Pereira
doi://10.26678/ABCM.COBEM2021.COB2021-1706
Abstract
Several research centers are designing aerospace vehicles for flight, in the Earth's atmosphere, at hypersonic speed, i.e., greater than five times the local speed of sound (M > 5), using airbreathing propulsion systems, based on supersonic combustion (scramjet technology). Aerospace hypersonic vehicles equipped with hypersonic airbreathing propulsion systems face extremely severe environments during the hypersonic flight in terms of thermal and aerodynamic loads. Thermal protection systems (TPS) and structural materials are the key techniques in hypersonic vehicle design. Hypersonic scramjet vehicles represent the future trends of access to space, passengers and merchandise transportations, and military (aircraft and/or weapons) applications, playing an important role in future aerospace hypersonic flight. From ballistic missiles and ballistic re-entry vehicles to hypersonic cruise and transatmospheric vehicles, flying within the Earth’s atmosphere, it requires thermal protection systems and specific structures technologies. In those cases, leading edges can reach temperatures even higher than 2000°C (2273.15 K), thus special materials are necessary for their thermal protection. In general, ceramic matrix composites (CMC), ultra-high temperature ceramics (UHTC), and superalloys are applied in hypersonic vehicle designs. In the present article, an overview of TPS and thermal management techniques were briefly discussed, with focus on rocket and airbreathing vehicles, which are needed to stand the aerodynamic heating, consequently, support the aerodynamic loads. Additionally, a brief review of the carbon-carbon composites (C/C), and carbon-silicon carbide composites (C/SiC) applied as passive thermal protection were presented. The advantages and limitations of these CMCs for hypersonic vehicle structures were also discussed, which may be applied to leading-to-trailing edges for hypersonic scramjet vehicles.
Keywords
hypersonic vehicle, High temperature, Thermal Protection System, hot structure
