月崎 竜童

レポート番号: STEP-2023-065

令和4年度宇宙輸送シンポジウム（2023年1月12日-13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 Symposium FY2022 (January 12-13, 2023. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan Observations of the upper atmosphere are of great scientific interest. When a satellite is used for such observations, a propulsion system is required to compensate for atmospheric drag. With existing propulsion systems, the observation period is limited by the propellant payload, and the lifetime of the satellite is limited to two to five years. An air-breathing ion engine (ABIE) has been proposed to solve this problem. The ABIE is a propulsion system that takes in the atmosphere around the satellite and uses it as propellant. Since the upper atmosphere is too rarefied to be used as a propellant, a mechanism to compress it is required. However, no air compression intake has been developed to meet the performance requirements of ABIE. Moreover, if the shape of the ion source, which is located downstream of the compression section as the propellant flow, changes, this compression performance may also change. In this study, an ion source was operated by ground air and the behavior of neutral particles in the ABIE was simulated by numerical simulations to investigate and compare the change in compression performance by changing the ion source geometry. 資料番号: SA6000184073 STEP-2022-021

令和4年度宇宙輸送シンポジウム（2023年1月12日-13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 Symposium FY2022 (January 12-13, 2023. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan The surface of a spacecraft equipped with a plasma propulsion system is subject to sputtering damage due to backflow ions. The authors reproduced the backflow ion flow by the Hybrid-PIC calculation method using the quasi-neutral electron fluid approximation and ion particles to evaluate the effect of backflow ion flow. The calculated results were compared with experimentally measured plasma potentials to confirm the validity of the model. The energy distribution function of backflow ions impacting the wall and incident angle distribution were obtained. Both results indicate that most of the backflow ions incident on the wall were produced just downstream of the thruster and impact at an acute angle to the wall. 資料番号: SA6000184099 STEP-2022-048