| Co-Investigator(Kenkyū-buntansha) |
高橋 和貴 東北大学, 工学研究科, 准教授 (80451491)
永岡 賢一 核融合科学研究所, ヘリカル研究部, 准教授 (20353443)
國中 均 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, 教授 (60234465)
小室 淳史 東北大学, 工学研究科, 助教 (70733137)
|
|---|
| Budget Amount *help |
¥41,600,000 (Direct Cost: ¥32,000,000、Indirect Cost: ¥9,600,000)
Fiscal Year 2017: ¥5,200,000 (Direct Cost: ¥4,000,000、Indirect Cost: ¥1,200,000)
Fiscal Year 2016: ¥5,330,000 (Direct Cost: ¥4,100,000、Indirect Cost: ¥1,230,000)
Fiscal Year 2015: ¥11,050,000 (Direct Cost: ¥8,500,000、Indirect Cost: ¥2,550,000)
Fiscal Year 2014: ¥20,020,000 (Direct Cost: ¥15,400,000、Indirect Cost: ¥4,620,000)
|
|---|
| Outline of Final Research Achievements |
Plasma flow dynamics in magnetic nozzle are investigated over wide ranges of several parameters such as a plasma density, ion and electron temperatures, and a plasma flow velocities by using a current-driven magnetoplasmadynamic (MPD) thruster and a current-free helicon plasma thruster. The experiments demonstrate that the spatial profile of the external discharge current is controllable for the MPD thruster by the magnetic field configuration; resulting in the improvement of the thruster performance. For the case of the helicon thruster, the Lorentz force due to the spontaneous azimuthal plasma current and the radial magnetic field of the nozzle is a key factor to increase the thrust imparted by the thruster. By combining these two concept of the thruster, the novel high power thruster called a helicon MPD thruster is also demonstrated in the laboratory experiments.
|
