@inproceedings{oai:jaxa.repo.nii.ac.jp:00016273,
 author = {大塚, 史子 and 羽田, 亨 and 篠原, 俊二郎 and 谷川, 隆夫 and 松岡, 健之 and Otsuka, Fumiko and Hada, Toru and Shinohara, Shunjiro and Tanikawa, Takao and Matsuoka, Takeshi},
 book = {平成24年度宇宙輸送シンポジウム: 講演集録, Proceedings of Space Transportation Symposium: FY2012},
 month = {Jan},
 note = {平成24年度宇宙輸送シンポジウム (2013年1月17日-1月18日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県, Space Transportation FY2012 (January 17-18, 2013. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, We have studied ion cyclotron resonance/ponderomotive acceleration (ICR/PA) for application to electrodeless electric thruster, by making use of test particle simulations. We estimate various statistics of acceleration process of ions such as the perpendicular and parallel energy gains, delta epsilon perpendicular and delta epsilon parallel, respectively, via the ICR and PA, the ion gyroradius, rho, increased by the ICR, and the index of the PA effect defined by R epsilon = 1 + delta epsilon parallel/delta epsilon perpendicular. These statistics can be scaled by the dimensionless parameter of the applied rf electric field intensity, e(sub 0) = E(sub 0) = Ω B(sub 0)R(sub 0), where E(sub 0) and B(sub 0) are the electric and magnetic field magnitude at the resonance, Ω is the ion gyrofrequency, and R(sub 0)(= 0.1 m) is a device radius of the chamber. We found that, when 1 less than e(sub 0) less than 4, delta epsilon parallel increases while delta epsilon perpendicular is constant with the increase in e(sub 0), and that the gyroradius is constant of approximately 0.35 m. This result suggest that, when we choose the device radius is larger than 0.35 m, the exhaust velocities of the ions can increase via the PA, keeping the ion wall-loss via the ICR being suppressed., 形態: カラー図版あり, 形態: PDF, Physical characteristics: Original contains color illustrations, Physical characteristics: PDF, 資料番号: AA0061856137, レポート番号: STEP-2012-054},
 publisher = {宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS), Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)},
 title = {イオンサイクロトロン共鳴: ポンデロモーティブ加速を利用した無電極電気推進の数値解析},
 year = {2013}
}