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International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.149 SNIP: 0.16 CiteScore™: 0.29

ISSN Imprimir: 2150-766X
ISSN En Línea: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.2019028270
pages 157-170


Yutaka Wada
Chiba Institute of Technology, Tsudanuma 2-17-1, Narashino, Chiba 275-0016, Japan
S. Hatano
Chiba Institute of Technology, Narashino, Chiba, 275-0016, Japan
Ayana Banno
Chiba Institute of Technology, Narashino, Chiba, 275-0016, Japan
Yo Kawabata
Chiba Institute of Technology, Narashino, Chiba, 275-0016, Japan
Hiroshi Hasegawa
NOF Corporation, Propellant and Explosive Research, Research and Development Department, Aichi Works, Taketoyo-Plant, 61-1, Kita-Komatsudani, Taketoyo, 470-2398, Aichi, Japan
T. Oda
NOF Corporation, Taketoyo, Aichi, 470-2379, Japan
Keiichi Hori
Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency (JAXA), 3-1-1 Yoshinodai, Chuo-Ku, Sagamihara, Kanagawa 252-5210, Japan


The development of a direct injection gas-hybrid rocket system using glycidyl azide polymer (GAP) as a solid fuel for the thrusters of very small satellites is described. Furthermore, a performance evaluation and the combustion characteristics of the propulsion system are presented. GAP is capable of self-decomposition and generates fuel-rich gas, which makes it viable as a fuel gas-hybrid power source for rockets. GAP also has a higher density compared to other polymers such as hydroxyl-terminated polybutadiene (HTPB), and the high-density specific impulse enables the development of a small thruster system. Gaseous oxygen was used as the oxidizer for the first test of the gas-hybrid rocket. The gas generator was tested using a 60 mm diameter motor with an end-burning GAP grain. The experimental combustion pressure was initially set at 1 MPa, and adjustments to the oxygen flow were made based on the test results of the gas-generator combustion. The resulting ignition smoothness and combustion stability were observed. Excellent characteristic velocity efficiency (90%)—larger than that of a classical hybrid rocket motor-was obtained. Moreover, quenching of the GAP gas generator was achieved after the oxidizer injection was stopped, which implies that this system has the capability of re-ignition.


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