TY - JOUR
T1 - Development study of precooled-cycle hypersonic turbojet engine for flight demonstration
AU - Sato, 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
N1 - Funding Information:
The first flight test for S-engine is to be conducted on the balloon-based operation vehicle (BOV) shown in Fig. 22 [2] . The vehicle mainly made of CFRP is approximately 5 m in length, 0.55 m in diameter and 500 kg in weight. Originally, BOV was design as a test bed for micro gravity experiments for more than 30 s with low costs, which is supported by Grant-in-Aid for JSPS fellows by Ministry of Education, Culture, Sports, Science and Technology in Japan. From 2005 to 2009, four vehicles will be developed step by step and the third one (BOV-3) will install S-engine in 2008 whose development schedule is shown in Table 2 .
PY - 2007/6
Y1 - 2007/6
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 frac(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-s free-fall, the vehicle pulls up and S-engine operates for 30 s at about Mach 2. High altitude tests of the engine components corresponding to the BOV's 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 frac(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-s free-fall, the vehicle pulls up and S-engine operates for 30 s at about Mach 2. High altitude tests of the engine components corresponding to the BOV's flight condition have been conducted.
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U2 - 10.1016/j.actaastro.2007.01.012
DO - 10.1016/j.actaastro.2007.01.012
M3 - Article
AN - SCOPUS:34248211635
SN - 0094-5765
VL - 61
SP - 367
EP - 375
JO - Acta Astronautica
JF - Acta Astronautica
IS - 1-6
ER -