太陽系惑星・衛星に存在する物資を推進剤に用いた定常作動型MPDスラスタの作動特性と高性能化

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

Magneto-Plasma-Dynamic (MPD) thrusters have been investigated in Osaka Sangyo University. The purpose of this study is to develop a practical MPD thruster system for future transportation among planets and satellites in the Solar System, especially for manned Mars exploration as one of the In-Space Transportation & Propulsion Project in collaboration with the Japan Aerospace eXploration Agency (JAXA). A magnetic field is applied to an MPD thruster by using permanent magnets of samarium cobalt (SmCo) magnets. In this study, performance characteristics were measured using special gases of carbon dioxide, methane and ammonia as original materials in planets and satellites in the Solar System; that is, propellant can be supplied just on the planets and satellites of Moon, Mars and Jupiter Moons; argon and nitrogen also used in basic experiments. Because operations with carbon dioxide and methane were slightly unstable compared with cases with other gases, the structure and operational condition should be examined to design a thruster suitable for transportation in the Solar System. Accordingly, the highest specific impulses of 444 and 560 sec, respectively, were obtain with CO2 and CH4 with 0.157 T although deposition of carbon was observed on the surface of the anode constrictor. Furthermore, a high performance with 5 mg/s of NH3 at 1.0 kW was a thrust of 60 mN, a specific impulse of 1,500 s and a thrust efficiency of 30.0% with 0.157 T. In high-power operation, a performance with 60 mg/s of NH3 at 6.75 kW was a thrust of 478 mN, a specific impulse of 810 s and a thrust efficiency of 19.0% with 0.157 T.

著者の誤記: Daisuke Tanaka

著者人数: 12名

資料番号: SA6000184075

STEP-2022-023