Abstract
This paper describes a development study of a precooled-cycle hypersonic turbojet engine for the first stage of TSTO space plane and hypersonic airplane. With reflecting the key technologies accumulated from ATREX (Expander cycle ATR engine) ground tests, the next flyable subscale engine "S-engine" is now developed. S-engine has 23 cm × 23 cm of rectangular cross section, 2.2 m of the overall length and about 100 kg of the weight employing a variable-geometry rectangular inlet and nozzle. It produces 1.2 kN of thrust at SLS, which corresponds to 1/4 of the ATREX engine. Design of the hypersonic components such as the inlet, precooler and nozzle has been finished and their aerodynamic performances were verified by wind tunnel tests and CFD analyses. A prototype model of the diagonal-flow compressor whose pressure ratio is 6 was manufactured. Its rotating tests under the very-low pressure conditions are now in progress. The reverse-flow annular combustion chamber was successfully tested. The first flight test of the S-engine is to be conducted in 2008 by the Balloon-based Operation Vehicle (BOV) which is about 5 m in length, 0.55 m in diameter and 500 kg in weight. The vehicle is dropped from an altitude of 40 km by a high altitude balloon. After 40-second free-fall, the vehicle pulls up and S-engine operates for 30 seconds at about Mach 2. High altitude tests of the engine components corresponding to the BOVs flight condition have been conducted.
| Original language | English |
|---|---|
| Title of host publication | AIAA 57th International Astronautical Congress, IAC 2006 |
| Pages | 6336-6343 |
| Number of pages | 8 |
| Volume | 9 |
| Publication status | Published - 2006 |
| Externally published | Yes |
| Event | AIAA 57th International Astronautical Congress, IAC 2006 - Valencia Duration: 2006 Oct 2 → 2006 Oct 6 |
Other
| Other | AIAA 57th International Astronautical Congress, IAC 2006 |
|---|---|
| City | Valencia |
| Period | 06/10/2 → 06/10/6 |
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ASJC Scopus subject areas
- Space and Planetary Science
- Aerospace Engineering
Cite this
Development study of precooled-cycle hypersonic turbojet engine for flight demonstration. / Satou, Tetsuya; Taguchi, Hideyuki; Kobayashi, Hiroaki; Kojima, Takayuki; Okai, Keiichi; Fujita, Kazuhisa; Masaki, Daisaku; Hongo, Motoyuki; Ohta, Toyohiko.
AIAA 57th International Astronautical Congress, IAC 2006. Vol. 9 2006. p. 6336-6343.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Development study of precooled-cycle hypersonic turbojet engine for flight demonstration
AU - Satou, Tetsuya
AU - Taguchi, Hideyuki
AU - Kobayashi, Hiroaki
AU - Kojima, Takayuki
AU - Okai, Keiichi
AU - Fujita, Kazuhisa
AU - Masaki, Daisaku
AU - Hongo, Motoyuki
AU - Ohta, Toyohiko
PY - 2006
Y1 - 2006
N2 - This paper describes a development study of a precooled-cycle hypersonic turbojet engine for the first stage of TSTO space plane and hypersonic airplane. With reflecting the key technologies accumulated from ATREX (Expander cycle ATR engine) ground tests, the next flyable subscale engine "S-engine" is now developed. S-engine has 23 cm × 23 cm of rectangular cross section, 2.2 m of the overall length and about 100 kg of the weight employing a variable-geometry rectangular inlet and nozzle. It produces 1.2 kN of thrust at SLS, which corresponds to 1/4 of the ATREX engine. Design of the hypersonic components such as the inlet, precooler and nozzle has been finished and their aerodynamic performances were verified by wind tunnel tests and CFD analyses. A prototype model of the diagonal-flow compressor whose pressure ratio is 6 was manufactured. Its rotating tests under the very-low pressure conditions are now in progress. The reverse-flow annular combustion chamber was successfully tested. The first flight test of the S-engine is to be conducted in 2008 by the Balloon-based Operation Vehicle (BOV) which is about 5 m in length, 0.55 m in diameter and 500 kg in weight. The vehicle is dropped from an altitude of 40 km by a high altitude balloon. After 40-second free-fall, the vehicle pulls up and S-engine operates for 30 seconds at about Mach 2. High altitude tests of the engine components corresponding to the BOVs flight condition have been conducted.
AB - This paper describes a development study of a precooled-cycle hypersonic turbojet engine for the first stage of TSTO space plane and hypersonic airplane. With reflecting the key technologies accumulated from ATREX (Expander cycle ATR engine) ground tests, the next flyable subscale engine "S-engine" is now developed. S-engine has 23 cm × 23 cm of rectangular cross section, 2.2 m of the overall length and about 100 kg of the weight employing a variable-geometry rectangular inlet and nozzle. It produces 1.2 kN of thrust at SLS, which corresponds to 1/4 of the ATREX engine. Design of the hypersonic components such as the inlet, precooler and nozzle has been finished and their aerodynamic performances were verified by wind tunnel tests and CFD analyses. A prototype model of the diagonal-flow compressor whose pressure ratio is 6 was manufactured. Its rotating tests under the very-low pressure conditions are now in progress. The reverse-flow annular combustion chamber was successfully tested. The first flight test of the S-engine is to be conducted in 2008 by the Balloon-based Operation Vehicle (BOV) which is about 5 m in length, 0.55 m in diameter and 500 kg in weight. The vehicle is dropped from an altitude of 40 km by a high altitude balloon. After 40-second free-fall, the vehicle pulls up and S-engine operates for 30 seconds at about Mach 2. High altitude tests of the engine components corresponding to the BOVs flight condition have been conducted.
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UR - http://www.scopus.com/inward/citedby.url?scp=40749153498&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:40749153498
SN - 9781605600390
VL - 9
SP - 6336
EP - 6343
BT - AIAA 57th International Astronautical Congress, IAC 2006
ER -