@inproceedings{oai:jaxa.repo.nii.ac.jp:00016503,
 author = {岡田, 佳祐 and 土本, 浩祐 and 増田, 祐輔 and 小泉, 宏之 and 中野, 正勝 and 荒川, 義博 and Okada, Keisuke and Tsuchimoto, Kosuke and Masuda, Yusuke and Koizumi, Hiroyuki and Nakano, Masakatsu and Arakawa, Yoshihiro},
 book = {平成22年度宇宙輸送シンポジウム: 講演集録, Proceedings of Space Transportation Symposium: FY2010},
 month = {},
 note = {平成22年度宇宙輸送シンポジウム(2011年1月20-21日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, Space Transportation FY2010 (January 20-21, 2011. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)), Sagamihara, Kanagawa Japan, The authors have developed a laser ignition micro solid rocket which is a propulsion device suitable for small spacecraft. To improve the performance of the micro solid rocket, several different materials were examined as the combustion chamber and nozzle. The materials tested here were SUS304, copper, aluminum, epoxy resin, acrylic resin and PTFE. As a result of impulse measurement, the micro solid rocket using PTFE is showed best performance and its specific impulse was 108 s. Weight of the micro solid rockets were measured before and after the combustion. This showed the mass exhausted from the metal micro solid rocket was less than initial propellant mass. On the other hand, in the case of resin rocket, the exhausted mass was more than the initial propellant. Temperature of the micro rocket body was measured to estimate the thermal energy loss. Difference of the estimated loss was within 10 % among metal rockets., 形態: カラー図版あり, 形態: CD-ROM1枚, Physical characteristics: Original contains color illustrations, Note: One CD-ROM, 資料番号: AA0065073056},
 publisher = {宇宙航空研究開発機構宇宙科学研究所, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)},
 title = {レーザー着火マイクロ固体ロケットの 燃焼室及びノズル材料に関する基礎実験},
 year = {2011}
}