日本航空宇宙学会論文集
Online ISSN : 2432-3691
Print ISSN : 1344-6460
論文
小惑星探査機「はやぶさ」搭載マイクロ波放電式イオンエンジンの初期運用
國中 均西山 和孝清水 幸夫都木 恭一郎川口 淳一郎上杉 邦憲
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2004 年 52 巻 602 号 p. 129-134

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The microwave discharge ion engine generates plasmas of the main ion source as well as the neutralizer using 4GHz microwave without discharge electrodes and hollow cathodes, so that long life and durability against oxygen and air are expected. MUSES-C “HAYABUSA” spacecraft installing four microwave discharge ion engines was launched into deep space by M-V rocket on May 9, 2003. After vacuum exposure and several runs of baking for reduction of residual gas the ion engine system established the continuous acceleration of the spacecraft toward an asteroid. The Doppler shift measurement of the communication microwave revealed the performance of ion engines, which is 8mN thrust force for a single unit with 3,200sec specific impulse at 23mN/kW thrust power ratio. At the beginning of December 2003 the accumulated operational time exceeded 7,000 hours and units.

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© 2004 The Japan Society for Aeronautical and Space Sciences
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