Proceedings of the Korean Society of Propulsion Engineers Conference (한국추진공학회:학술대회논문집)
- 2004.03a
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- Pages.593-596
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- 2004
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- 1975-342X(pISSN)
COMBUSTION CHARACTERISTICS OF A MICRO-SOLID PROPELLANT ROCKET ARRAY THRUSTER
- Kazuyuki Kondo (Department of Mechatronics and Precision Engineering, Tohoku University) ;
- Shuji Tanaka (Department of Mechatronics and Precision Engineering, Tohoku University) ;
- Hiroto Habu (The Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency (JAXA) ;
- Tokudome, Shin-ichiro (The Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency (JAXA) ;
- Keiichi Hori (The Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency (JAXA) ;
- Hirobumi Saito (The Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency (JAXA) ;
- Akihito Itoh (Nichiyu Giken Kogyo Co., Lt) ;
- Masashi Watanabe (Nichiyu Giken Kogyo Co., Lt) ;
- Masayoshi Esashi (New Industry Creation Hatchery Center (NICHe), Tohoku University)
- Published : 2004.03.01
Abstract
We are developing a micro-solid propellant rocket array thruster for simple attitude control of a 10 kg class micro-spacecraft. The prototype has ø 0.8 mm solid propellant micro-rockets arrayed at a pitch of 1.2 mm on a 22 x 22 mm substrate. In previous studies, an impulse thrust of 4.6 x 10