| Project/Area Number |
24760669
|
|---|
| Research Category |
Grant-in-Aid for Young Scientists (B)
|
| Allocation Type | Multi-year Fund |
|---|
| Research Field |
Aerospace engineering
|
|---|
| Research Institution | Akashi National College of Technology |
|---|
Principal Investigator |
|
|---|
| Project Period (FY) |
2012-04-01 – 2014-03-31
|
| Project Status |
Completed (Fiscal Year 2013)
|
| Budget Amount *help |
¥4,550,000 (Direct Cost: ¥3,500,000、Indirect Cost: ¥1,050,000)
Fiscal Year 2013: ¥1,820,000 (Direct Cost: ¥1,400,000、Indirect Cost: ¥420,000)
Fiscal Year 2012: ¥2,730,000 (Direct Cost: ¥2,100,000、Indirect Cost: ¥630,000)
|
|---|
| Keywords | 電気推進 / 磁気ノズル / 磁気プラズマセイル / 数値シミュレーション / ハイブリッド粒子シミュレーション / 宇宙推進 / プラズマセイル / 3次元ハイブリッドモデル |
|---|
| Research Abstract |
Magneto Plasma Sail (MPS) is a propulsion system used in space, which generates its force by the interaction between solar wind and an inflated magnetic field via a plasma injection. The magnetic nozzle can control the plasma flow resulting from expanded thermal plasma by using a coil and it obtains the thrust by exhausting the plasma flow from the back of the rocket. As a results by using numerical simulations, the optimized injected thermal plasma beta is 0.46 and the ratio of Larmor radius of injected ion to the representative length of the magnetic field is 3 at the injection point. In this situation, the maximum thrust gain of the MPS with the magnetic nozzle is 5 compared with the thrust obtained from only magnetic nozzle.
The thrust gain of the MPS with magnetic nozzle is 3 in case for the ground experiment under the same parameters optimized by the numerical simulation. In the present study, the thrust gain is successfully observed in the ground experiment.
|
