Concept Study of High-reliable LH2/LOX Rocket Engine for Reusable Experimental Vehicle
- Paper number
IAC-05-C4.1.08
- Author
Mr. Hiroshi Aoki, Japan Aerospace Exploration Agency (JAXA), Japan
- Coauthor
Mr. Moriyasu Fukuzoe, Japan Aerospace Exploration Agency (JAXA), Japan
- Coauthor
Dr. Yoshihiro Naruo, Japan Aerospace Exploration Agency (JAXA)/ISAS, Japan
- Coauthor
Mr. Masaaki Yasui, Mitsubishi Heavy Industries, Ltd., Japan
- Coauthor
Mr. Hirotaka Kure, Ishikawajima-Harima Heavy Industries Co.,Ltd., Japan
- Coauthor
Mr. Takeshi Kanda, Japan Aerospace Exploration Agency (JAXA/Kakuda Research Center), Japan
- Coauthor
Dr. Keiichi Hasegawa, Japan Aerospace Exploration Agency (ISTA/JAXA), Japan
- Year
2005
- Abstract
Future Space Transportation Group of Japan Aerospace Exploration Agency plans to develop and test a Reusable Experimental vehicle. Repeatable use with short turn-around, abort-ability and development of a vehicle with high reliability are objectives of this research. A new LH2/LOX rocket engine system plans to be developed. The vehicle consists of four thrust chambers and two or four turbopumps, required 80kN level total thrust and throttling capability to 40 Separation in the nozzle is inhibited even under the throttling condition. Specific impulse of 3600 m/s is required. Conceptual study was conducted prior to design and production of the engine. In the study, three engine cycles were applied to the new engine, that is, the coolant-bleed (CB) cycle, the expander (EX) cycle and the partial-bleed-expander (PBE) cycle. Exchanged heat amount and pressure loss of the coolant LOX in the chamber and nozzle were calculated along the cooling channel. Efficiencies of pumps and turbines were calculated based on specific speed and others. Properties of H2, O2 and combustion gas were calculated with gas property codes. Separation condition was calculated with the formula of Reshotko-Tucker and Lawrence. CB cycle attained highest chamber pressure in the three. However, partiality of the turbines was significantly small and a large amount of turbine gas, about 20
- Abstract document
- Manuscript document
IAC-05-C4.1.08.pdf (🔒 authorized access only).
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