Eventos Anais de eventos
ENCIT 2022
19th Brazilian Congress of Thermal Sciences and Engineering
Preliminary design of an aerospace vehicle using airbreathing propulsion system for hypersonic speed
Submission Author:
Laura Carolina Monteiro dos Santos Rodrigues da Silva , SP
Co-Authors:
Laura Carolina Monteiro dos Santos Rodrigues da Silva, Juan Pablo de Lima Costa Salazar, Eduardo De Carli da Silva, George Marinho, Paulo Toro
Presenter: Laura Carolina Monteiro dos Santos Rodrigues da Silva
doi://10.26678/ABCM.ENCIT2022.CIT22-0340
Abstract
In the process of developing new space technologies, it is important to have simple design tools capable of performing initial analyzes and serving as a basis for other studies and predicting possible problems in the development of the project. In this work, a simple tool was developed, implemented and applied in order to obtain the preliminary design of an aerospace vehicle using a hypersonic airbreathing propulsion system, based on supersonic combustion (scramjet) technology. For this case, a theoretical-analytical approach was used to determine the geometry for the scramjet vehicle, as well as to perform an analysis of the flow behavior. Hypotheses of one-dimensional, steady, and inviscid flow were considered and the flow behaved as a calorically perfect gas. The scramjet model was sectioned into compression section, combustion chamber and expansion section. In the compression section, the oblique shock wave theory was applied. To minimize the loss of performance during compression, the constant shock intensity criterion was adopted through the incident oblique shock waves. One-dimensional flow with heat addition (Rayleigh) theory was applied in the combustion chamber. To obtain the dimension of the expansion section, the area ratio theory was applied coupled with the expansion wave (Prandtl-Meyer) theory. To implement the developed tool and verify its results, a scramjet vehicle flying at 25 km of geometric altitude at Mach number 6.3 was considered. Therefore, the scramjet vehicle geometry was obtained, including the compression ramp angles and expansion ramp angle. Also, the flow thermodynamic (pressure, temperature and density) properties and flow Mach number were obtained for each section of the vehicle. Finally, other geometries can be obtained through the developed tool, changing the parameters, such as altitude, flight speed and other geometric parameters, and the preliminary geometry designed can work as a tool for future studies using computational fluid dynamics (CFD) and experimental investigations.
Keywords
supersonic combustion, hypersonic airbreathing propulsion, Scramjet, hypersonics
