Abstract
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
| Original language | English |
|---|---|
| Title of host publication | A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference |
| Pages | 1914-1922 |
| Number of pages | 9 |
| Volume | 3 |
| Publication status | Published - 2005 |
| Externally published | Yes |
| Event | 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference - Capua Duration: 2005 May 16 → 2005 May 20 |
Other
| Other | 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference |
|---|---|
| City | Capua |
| Period | 05/5/16 → 05/5/20 |
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ASJC Scopus subject areas
- Engineering(all)
Cite this
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. Vol. 3 2005. p. 1914-1922.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Design study on a small pre-cooled turbojet engine for flight experiments
AU - Taguchi, Hideyuki
AU - Satou, Tetsuya
AU - Kobayashi, Hiroaki
AU - Kojima, Takayuki
AU - Okai, Keiichi
AU - Fujita, Kazuhisa
AU - Ohta, Toyohiko
PY - 2005
Y1 - 2005
N2 - 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
AB - 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
UR - http://www.scopus.com/inward/record.url?scp=29044441429&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=29044441429&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:29044441429
SN - 1563477297
SN - 9781563477294
VL - 3
SP - 1914
EP - 1922
BT - A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference
ER -