Multidisciplinary Design Optimization of a Two-Stage-to-Orbit Reusable Launch Vehicle with Ethanol-Fueled Rocket-Based Combined Cycle Engines

A fully reusable two-stage-to-orbit launch vehicle with ethanol-fueled rocket-based combined cycle (RBCC) engines has been studied in Japan as a promising option for future space transportation system. In this paper, a conceptual design study of such a vehicle is conducted using multidisciplinary de...

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Veröffentlicht in:	TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 2017, Vol.60(5), pp.265-275
Hauptverfasser:	FUJIKAWA, Takahiro, TSUCHIYA, Takeshi, TOMIOKA, Sadatake
Format:	Artikel
Sprache:	eng
Schlagworte:	Aerospace engines Ascent trajectories Computer simulation Conceptual Design Study Design optimization Ethanol Future Space Transportation System Hypersonic flight Launch vehicles Low earth orbits Mathematical models Multidisciplinary Design Optimization Propulsion Reusable launch vehicles Rocket-Based Combined Cycle Engine Rocket-based combined-cycle engines Space transportation system Static stability Trajectory analysis Transportation systems Two stage to orbit vehicles Two-Stage-to-Orbit Reusable Launch Vehicle
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