TY - GEN
T1 - Research and development of ramjet engine for high-mach integrated control experiment (HIMICO)
AU - Wakabayashi, Sho
AU - Yoshida, Hidekazu
AU - Chiga, Takahiro
AU - Sato, Tetsuya
AU - Taguchi, Hideyuki
AU - Kojima, Takayuki
AU - Okamoto, Toshiki
AU - Ikeda, Yutaka
AU - Nakaya, Shinji
AU - Tsue, Mitsuhiro
N1 - Publisher Copyright:
© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2018
Y1 - 2018
N2 - The HIMICO (High-Mach Integrated Control experiment) project is under way by universities and JAXA. The purposes are to establish the flying test bed of hypersonic flight experiments and to demonstrate the integration control technology of the airframe and the engine. Currently, the performance of the ramjet engine for HIMICO is being acquired and improved. Two kinds of verification experiment are shown here: a supersonic wind tunnel test and a combustion test. On the supersonic wind tunnel test, the performance maps of the air-intake are acquired at Mach 3.0, 3.4 and 3.8. The condition of the buzz occurring is investigated. We should decide the flight experimental conditions of the engine under which the buzz does not occur. With an angle of sideslip (AOS), the secondary flow which is caused by sidewalls reduces the air-intake performance: total pressure recovery and mass capture ratio. Both theoretical and atheoretical oblique shock waves are generated on the 1st ramp. This state causes the air-intake performance deterioration. On the combustion test, heat tolerance of the thermal insulator and the ignition with the igniter are confirmed. The measured maximum combustion temperature is 1138 K. We plan to conduct a system firing test using the ramjet test facility (RJTF) in JAXA to obtain the integrated performance for the first flight experiment.
AB - The HIMICO (High-Mach Integrated Control experiment) project is under way by universities and JAXA. The purposes are to establish the flying test bed of hypersonic flight experiments and to demonstrate the integration control technology of the airframe and the engine. Currently, the performance of the ramjet engine for HIMICO is being acquired and improved. Two kinds of verification experiment are shown here: a supersonic wind tunnel test and a combustion test. On the supersonic wind tunnel test, the performance maps of the air-intake are acquired at Mach 3.0, 3.4 and 3.8. The condition of the buzz occurring is investigated. We should decide the flight experimental conditions of the engine under which the buzz does not occur. With an angle of sideslip (AOS), the secondary flow which is caused by sidewalls reduces the air-intake performance: total pressure recovery and mass capture ratio. Both theoretical and atheoretical oblique shock waves are generated on the 1st ramp. This state causes the air-intake performance deterioration. On the combustion test, heat tolerance of the thermal insulator and the ignition with the igniter are confirmed. The measured maximum combustion temperature is 1138 K. We plan to conduct a system firing test using the ramjet test facility (RJTF) in JAXA to obtain the integrated performance for the first flight experiment.
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U2 - 10.2514/6.2018-5319
DO - 10.2514/6.2018-5319
M3 - Conference contribution
AN - SCOPUS:85056174855
SN - 9781624105777
T3 - 22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference
BT - 22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference, 2018
Y2 - 17 September 2018 through 19 September 2018
ER -