@inproceedings{oai:jaxa.repo.nii.ac.jp:00002935,
 author = {小澤, 宇志 and 今村, 俊介 and 西山, 和孝 and 田川, 雅人 and 藤田, 和央 and Ozawa, Takashi and Imamura, Shunsuke and Nishiyama, Kazutaka and Tagawa, Masahito and Fujita, Kazuhisa},
 book = {宇宙航空研究開発機構特別資料: 第50回流体力学講演会/第36回航空宇宙数値シミュレーション技術シンポジウム論文集, JAXA Special Publication: Proceedings of the 50th Fluid Dynamics Conference / the 36th Aerospace Numerical Simulation Symposium},
 month = {Feb},
 note = {第50回流体力学講演会/第36回航空宇宙数値シミュレーション技術シンポジウム (2018年7月4日-6日. 宮崎市民プラザ), 宮崎市, 宮崎, 50th Fluid Dynamics Conference /the 36th Aerospace Numerical Simulation Symposium (July 4-6, 2018. Miyazaki Citizen's Plaza), Miyazaki, Japan, At Japan Aerospace Exploration Agency (JAXA), the Super Low Altitude Test Satellite (SLATS), launched in 2017, has been expected to extend space utilization into extremely low earth orbits. Because of the increase of aerodynamic forces acting on the satellite along with the descent of altitude, ion engines have been used for the purpose of maintaining the altitude and attitude of the satellite. To improve the duration of satellites in super low altitude range, the air breathing ion engine (ABIE) has been proposed for future missions. In this work, by carrying out direct simulation Monte Carlo computations, we investigate intake performance for ABIE, especially at 268 km altitude, which is a sun-synchronous recurrent orbit for SLATS., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1830029006, レポート番号: JAXA-SP-18-005},
 pages = {97--101},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {空気吸込式イオンエンジンの実証に向けたエアインテーク数値解析},
 volume = {JAXA-SP-18-005},
 year = {2019}
}