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International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.142 SNIP: 0.16 CiteScore™: 0.29

ISSN 印刷: 2150-766X
ISSN オンライン: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.v8.i4.50
pages 321-327

MICRO SOLID PROPELLANT THRUSTER FOR SMALL SATELLITE

Akihito Itoh
Nichiyu Giken Kogyo Co.,Ltd, 21-2 Matoba-shinmachi, Kawagoe, Saitama 350-1107, Japan
Masashi Watanabe
Nichiyu Giken Kogyo Co.,Ltd, 21-2 Matoba-shinmachi, Kawagoe, Saitama 350-1107, Japan
Hiroto Habu
Japan Aerospace Exploration Agency (JAXA), 3-1-1 Yoshinodai, Chuo-Ku, Sagamihara, Kanagawa 252-5210, Japan
Shin-Ichiro Tokudome
The Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency (JAXA), 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
Hirobumi Saito
The Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency (JAXA), Japan
Kazuyuki Kondo
Department of Nanomechanics, Graduate School of Engineering, Tohoku University 6-6-01 AzaAoba, Aramaki, Aoba-ku, Sendai, Miyagi 980-8579, Japan
Shuji Tanaka
Department of Nanomechanics, Graduate School of Engineering, Tohoku University 6-6-01 AzaAoba, Aramaki, Aoba-ku, Sendai, Miyagi 980-8579, Japan
Masayoshi Esashi
Department of Nanomechanics, Graduate School of Engineering, Tohoku University 6-6-01 AzaAoba, Aramaki, Aoba-ku, Sendai, Miyagi 980-8579, Japan

要約

A micro solid propellant thruster for simple attitude control of a 10 kg class small spacecraft is currently under development. The prototype has ∅ 0.8 mm micro rocket elements, arrayed at a pitch of 1.2 mm on a 22 × 22 mm substance. Initially, solid propellants were used, obtaining only 20% ignition probability with a very long ignition delay (e.g. 1000 ms) as well as very high ignition energy. While observing the tested prototype sample, it became apparent that the main cause of these problems was a gap between the solid propellants and ignition heater. So, the thruster system was improved so that the propellants adhered to the heater. In addition, an ignition charge was used that starts to burn at 210°C, which was acetone having the form of slurry. As a result, a better ignition probability of over 80% in vacuum and half thrust of expectation were gained.

参考

  1. David, Jr., H.L., Siegfried, W.J, Ronald, B.C., and Erik, K.A., Digital Micropropulsion.

  2. Daniel, W.Y., Son, T.L., Edgar,C., Jamie, B.N., Robert, III, E. B., Kenneth, J.G., Dave, F., Rodney, L., and Xiaoyang, Z., MEMS Mega-Pixel Micro-Thruster Arrays for Small Satellite Stationkeeping.

  3. Rossi, C., Orieux, S., Larangot, B., Do Conto, T., and Estéve, D., Design, Fabrication and Modeling of Solid Propellant Microrocket-Application to Micropropulsion.

  4. Rossi, C., Chaalane, A., Larangot, B., Conédéra, V., Briand, D., Pham, P.-Q., de Rooij, N.F., Köhler, J., Eriksson, A.B., Jonsson, K., Kratz, H., Puig-Vidal, M., Miribel-Català, P., and Samitier, J., Pyrotechnical Microthrusters for Space Application.

  5. Zhang, K.L., Chou, S.K., and Ang, S.S., Development of a Solid Propellant Microthruster with Chamber and Nozzle Etched on a Wafer Surface.


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