Conceptual design of a Two-Stage-To-Orbit vehicle using SABRE engines
| Autor: | BREVAULT, L., BALESDENT, M., WUILBERCQ, R., SUBRA, N., ORIOL, S., BONNAL, C., DODDS, M., TAYLOR, N., VARVILL, R. |
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| Přispěvatelé: | DTIS, ONERA, Université Paris Saclay (COmUE) [Palaiseau], ONERA-Université Paris Saclay (COmUE), Centre National d'Etudes Spatiales - Direction Des Lanceurs. (CNES), Reaction Engines Ltd |
| Jazyk: | angličtina |
| Rok vydání: | 2019 |
| Předmět: |
[PHYS]Physics [physics]
0209 industrial biotechnology LAUNCH VEHICLE DESIGN 02 engineering and technology MDO 7. Clean energy 01 natural sciences 010305 fluids & plasmas [SPI]Engineering Sciences [physics] 020901 industrial engineering & automation AEROSPACE VEHICLE DESIGN 0103 physical sciences LANCEUR REUTILISABLE MULTI-DISCIPLINARY OPTIMIZATION AEROSPACE PROPULSION NUMERICAL SIMULATION AEROBIE [INFO]Computer Science [cs] [MATH]Mathematics [math] |
| Zdroj: | EUCASS 2019 EUCASS 2019, Jul 2019, MADRID, Spain. ⟨10.13009/EUCASS2019-454⟩ |
| DOI: | 10.13009/EUCASS2019-454⟩ |
| Popis: | International audience; The French Space Agency (Centre National d'Etudes Spatiales-CNES), the UK Space Agency (UKSA), Reaction Engines Limited (REL) and the French Aerospace Lab (Office National d'Etudes et de Recherches Aérospatiales-ONERA) share a common interest for future space launch architectures and technologies. Preliminary results of a joint study are presented in this paper with the main objective of assessing and quantifying the potential advantages and benefits of air-breathing propulsion technology developed by REL named SABRE (Synergetic Air-Breathing Rocket Engine) for future launch architectures. In that purpose, a conceptual study of two alternative Two-Stage-To-Orbit (TSTO) vehicles is carried out using the SABRE air-breathing rocket engine and a LOx/CH4 rocket engine (for the second stage) for the injection of a 15t payload into low Earth orbit. Different analyses are carried out using a coupled multidisciplinary process involving propulsion, aerodynamics, sizing and trajectory optimizations. Some key influential parameters and intricate behaviors are analyzed through sensitivity to the stage separation conditions. As a result, these analyses provide insight into technological requirements to achieve the target mission using these types of advanced propulsion technologies. |
| Databáze: | OpenAIRE |
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