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International Journal of Energetic Materials and Chemical Propulsion

ISSN Print: 2150-766X
ISSN Online: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.2017011994
pages 435-451

DEVELOPMENT OF TEST FACILITIES FOR 5 KN-THRUST HYBRID ROCKET ENGINES AND A SWIRLING-OXIDIZER-FLOW-TYPE HYBRID ROCKET ENGINE FOR TECHNOLOGY DEMONSTRATION

Koki Kitagawa
Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Chuo-ku, Sagamihara, Kanagawa 252-5210, Japan; The University of Tokyo, 7-3-1 Hongo, Bunkyo-ku, Tokyo 113-0033, Japan
Saburo Yuasa
Tokyo Metropolitan University, 6-6 Asahigaoka, Hino-city, Tokyo, 191-0065, Japan
Takashi Sakurai
Tokyo Metropolitan University, 6-6 Asahigaoka, Hino-city, Tokyo, 191-0065, Japan
S. Hatagaki
Tokyo Metropolitan University, 6-6 Asahigaoka, Hino-city, Tokyo, 191-0065, Japan
N. Shiraishi
Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Chuo-ku, Sagamihara, Kanagawa 252-5210, Japan; The University of Tokyo, 7-3-1 Hongo, Bunkyo-ku, Tokyo 113-0033, Japan
H. Ando
Tokyo Metropolitan University, 6-6 Asahigaoka, Hino-city, Tokyo, 191-0065, Japan
Takeshi Yagishita
Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency (JAXA), 3-1-1, Yoshinodai, Sagamihara, Kanagawa, 229-8510, Japan
N. Suzuki
Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Chuo-ku, Sagamihara, Kanagawa 252-5210, Japan
A. Takayama
Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Chuo-ku, Sagamihara, Kanagawa 252-5210, Japan; The University of Tokyo, 7-3-1 Hongo, Bunkyo-ku, Tokyo 113-0033, Japan
R. Yui
Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Chuo-ku, Sagamihara, Kanagawa 252-5210, Japan; The University of Tokyo, 7-3-1 Hongo, Bunkyo-ku, Tokyo 113-0033, Japan
T. Shimada
Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Chuo-ku, Sagamihara, Kanagawa 252-5210, Japan; The University of Tokyo, 7-3-1 Hongo, Bunkyo-ku, Tokyo 113-0033, Japan

ABSTRACT

At the Hybrid Rocket research Working Group, performing demonstrations of current technologies is pursued. The target thrust was set as 5 kN and a hybrid rocket test engine program (HTE-5-1) was initiated. To demonstrate the hybrid rocket engine technology, a hybrid rocket test facility was designed at the Akiruno facility, which belongs to the Japan Aerospace Exploration Agency. A low- flow rate gaseous oxygen (GOX) feed system that includes a purge system, test stand, measurement system, and control system was manufactured. The operability and functionality, such as the GOX mass flow range and natural frequency of the test stand, were examined. It was confirmed that combustion tests under a condition of up to 0.5 kg/s GOX mass flow rate could be conducted. A 5-kN-thrust swirling-oxidizer-flow-type hybrid rocket engine using a GOX/polypropylene propellant was designed and manufactured as a demonstrator. Two combustion tests were performed with the demonstration engine under conditions below the design point. Reliable ignition and stable combustion for long durations were achieved, and accurate experimental data were obtained. This demonstrated the effectiveness of the combustion test and validated the suitability of our engine design method. It was confirmed that the combustion test could be performed safely and properly using the new test facility and demonstrator.