@misc{oai:jaxa.repo.nii.ac.jp:00002861,
 author = {村中, 崇信 and 永田, 拓雅 and 長原, 拓哉 and 永井, 宏樹 and Muranaka, Takanobu and Nagata, Takuma and Nagahara, Takuya and Nagai, Hiroki},
 month = {Mar},
 note = {第8回スペースデブリワークショップ (2018年12月3-5日. 宇宙航空研究開発機構調布航空宇宙センター(JAXA)(CAC)), 調布市, 東京, The 8th Space Debris Workshop (December 3-5, 2018. Chofu Aerospace Center, Japan Aerospace Exploration Agency (JAXA)(CAC)), Chofu, Tokyo, Japan, 本研究では, 帯電薄膜を利用した抗力増大装置によるデブリの軌道遷移技術を開発し, 地表高度800kmから1000kmの混雑軌道における大型デブリ除去実証に適用することを目指している. その原理は, 電離層に存在する希薄大気の抗力を利用するもので, 地表高度400kmから600km程度の低軌道衛星軌道遷移に利用される原理と等しい. 大気の効力は動圧に比例するが, 除去対象の大型デブリが存在する高度1000kmの大気密度は600kmおよび400kmのそれらと比較して, それぞれ1/50 および1/100 であり, 抗力もそれぞれ1/50 および1/100 程度である. そこで本研究では, 1m 四方から3m 四方程度の薄膜を抗力発生装置とし, これを帯電させることで高層待機中に多く存在するイオンによる効力を増大し, 地表高度600km 程度の大気抵抗と同等の効力を発生させる衛星コンポーネントの開発を目指す. ここでは, 本システムの基本原理と, 電離層プラズマ中におけるイオンによる効力発生の基礎となる, 薄膜電位周辺の電位構造と薄膜が収集するイオン電流について, 数値シミュレーションによる解析結果を紹介する., Expansion of space utilization activities increases the number of large-scale debris like an upper stage of the launch vehicle in congested orbit at altitude of 800-1000 km. These debris collide with others producing a lot of smaller debris that would cause further collisions to spacecrafts and their destruction in orbit. For these reasons, some low-cost debris removal systems are proposed, and a part of fundamental technologies had already been demonstrated by space agencies in space. The atmosphere at the altitude of 800-1000 km is composed of neutral particles of He, H, O and ions of O+, H+. One of the conventional de-orbit system uses a deployable sail capturing the neutral particles to produce a drag force which had already been demonstrated on-orbit at the altitude of 400 to 600 km. The drag force decreases orbital velocity of a spacecraft and then the spacecraft will move to the lower orbit to the earth. This type of de-orbit system is very simple, but a large-scale structure is necessary to produce enough drag force for a large-scale debris. In this research, we focus on the ions existing in the atmosphere at high altitude to enhance the drag force for the removal system. The concept of de-orbit system utilize an ion sheath generated by a charged deployable thin film whose scale is considered to be 1 m×1 m to 3 m×3 m. In this paper, as a preliminary study, we introduce the fundamentals of the debris removal system using the charged membrane. The performance of the system is also discussed as the variations of the atmospheric environment in LEO, and the potential structure around the charged membrane is analyzed by a 3D full particle electrostatic code to determine a proper method to bias the membrane., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1830034057, レポート番号: JAXA-SP-18-011},
 title = {Orbit Transition of Large-scale Debris Using Drag Force Intensifier Applying Charged Membrane},
 year = {2019}
}