Study of MPD Thruster System for Future High-power Space Explorations

2016 Fiscal Year Final Research Report

• Project/Area Number: 26289328
• Research Category: Grant-in-Aid for Scientific Research (B)
• Allocation Type: Partial Multi-year Fund
• Section: 一般
• Research Field: Aerospace engineering
• Research Institution: Japan Aerospace EXploration Agency
• Principal Investigator: Funaki Ikkoh 国立研究開発法人宇宙航空研究開発機構, 宇宙科学研究所, 准教授 (50311171)
• Co-Investigator(Kenkyū-buntansha): 堀澤 秀之 東海大学, 工学部, 教授 (30256169) ; 奥野 喜裕 東京工業大学, 総合理工学研究科(研究院), 教授 (10194507)
• Research Collaborator: OSHIO Yuya 東京農工大学, 工学研究科, 助教 (80711233) ; KUBOTA Kenichi 国立研究開発法人宇宙航空研究開発機構, 航空技術部門, 研究員 ; KAWASAKI Akira 名古屋大学, 大学院工学研究科, 助教 ; MIYAZAKI Kenji 東海大学, 大学院・工学研究科, 大学院生 ; TONOOKA Satoshi 総合研究大学院大学, 物理科学研究科, 大学院生 ; TAUCHI Shitan 総合研究大学院大学, 物理科学研究科, 大学院生
• Project Period (FY): 2014-04-01 – 2017-03-31
• Keywords: 航空宇宙工学 / プラズマ・核融合 / 宇宙機推進 / MPDアークジェット / 有人惑星探査

Outline of Final Research Achievements

For an orbital transfer from the Earth to Mars, a high power and high performance spacecraft electric propulsion system is required in particular for a cargo-vehicle since electric propulsion's high specific impulse enables a large payload ratio, and hence a large mass can be conveyed to Mars within limited launch vehicle capability. In this study, 100-N-class Magnetoplasmadynamic (MPD) arcjet system was conceptually designed, and the thruster head design was experimentally demonstrated by using a pulsed operation, in which a capacitor bank as a power source. Such an test can prevent a steady operation that requires large and continuous power and vacuum facilities.

Free Research Field

宇宙工学