Design study on a small pre-cooled turbojet engine for flight experiments

Hideyuki Taguchi, Tetsuya Satou, Hiroaki Kobayashi, Takayuki Kojima, Keiichi Okai, Kazuhisa Fujita, Toyohiko Ohta

研究成果: Conference contribution

8 引用 (Scopus)

抄録

Design aspects of a small pre-cooled turbojet engine for flight experiments are investigated in this study. Pre-cooled turbojet engine is a hypersonic engine suitable for Two Stage To Orbit (TSTO) Space Planes and other hypersonic cruise vehicles. The engine has a capability to accelerate vehicles with a flight speed range between Mach 0 and 6. The payload injection capability of the vehicle appeared to be higher than that with rocket engines, in the former analysis. Some component models for the engine have been tested under simulated conditions. Aerodynamic performances of a variable air intake have been investigated by wind tunnel tests. Anti-frosting technology has been established by using a light weight pre-cooler. System performance of pre-cooling cycle under sea level static condition has been obtained. High temperature structure for a ram combustor and a variable exhaust nozzle has been examined by firing tests. A small pre-cooled turbojet engine for flight experiments is designed based on the component models. The engine will be used for the experiments to obtain thenno-dynamic data of the pre-cooled cycle with the designed flight speed range. Results of thermo-dynamic analyses, CFD analyses and component tests are described in this study. Those results are used to determine the final scale and shape of each component

元の言語English
ホスト出版物のタイトルA Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference
ページ1914-1922
ページ数9
3
出版物ステータスPublished - 2005
外部発表Yes
イベント13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference - Capua
継続期間: 2005 5 162005 5 20

Other

Other13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference
Capua
期間05/5/1605/5/20

Fingerprint

Turbojet engines
Engines
Hypersonic aerodynamics
Experiments
Air intakes
Rocket engines
Sea level
Combustors
Mach number
Wind tunnels
Nozzles
Aerodynamics
Computational fluid dynamics
Orbits
Cooling
Temperature

ASJC Scopus subject areas

  • Engineering(all)

これを引用

Taguchi, H., Satou, T., Kobayashi, H., Kojima, T., Okai, K., Fujita, K., & Ohta, T. (2005). Design study on a small pre-cooled turbojet engine for flight experiments. : A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference (巻 3, pp. 1914-1922)

Design study on a small pre-cooled turbojet engine for flight experiments. / Taguchi, Hideyuki; Satou, Tetsuya; Kobayashi, Hiroaki; Kojima, Takayuki; Okai, Keiichi; Fujita, Kazuhisa; Ohta, Toyohiko.

A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference. 巻 3 2005. p. 1914-1922.

研究成果: Conference contribution

Taguchi, H, Satou, T, Kobayashi, H, Kojima, T, Okai, K, Fujita, K & Ohta, T 2005, Design study on a small pre-cooled turbojet engine for flight experiments. : A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference. 巻. 3, pp. 1914-1922, 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference, Capua, 05/5/16.
Taguchi H, Satou T, Kobayashi H, Kojima T, Okai K, Fujita K その他. Design study on a small pre-cooled turbojet engine for flight experiments. : A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference. 巻 3. 2005. p. 1914-1922
Taguchi, Hideyuki ; Satou, Tetsuya ; Kobayashi, Hiroaki ; Kojima, Takayuki ; Okai, Keiichi ; Fujita, Kazuhisa ; Ohta, Toyohiko. / Design study on a small pre-cooled turbojet engine for flight experiments. A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference. 巻 3 2005. pp. 1914-1922
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