2005 Fiscal Year Final Research Report Summary
Investigation of Thrust Generation Mechanism of Magneto-plasma-sail
| Project/Area Number |
15360453
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| Research Category |
Grant-in-Aid for Scientific Research (B)
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| Allocation Type | Single-year Grants |
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| Section | 一般 |
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| Research Field |
Aerospace engineering
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| Research Institution | Japan Aerospace Exploration Agency |
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Principal Investigator |
OGAWA Hiroyuki Japan Aerospace Exploration Agency, Institute of Space and Astronautical Science, Associate Professor, 宇宙科学研究本部宇宙航行システム研究系, 助教授 (60311172)
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| Co-Investigator(Kenkyū-buntansha) |
FUNAKI Ikkoh Japan Aerospace Exploration Agency, Institute of Space and Astronautical Science, Associate Professor, 宇宙科学研究本部宇宙輸送工学研究系, 助教授 (50311171)
YAMAKAWA Hiroshi Japan Aerospace Exploration Agency, Institute of Space and Astronautical Science, Associate Professor, 宇宙科学研究本部宇宙航行システム研究系, 助教授 (50260013)
FUJITA Kazuhisa Japan Aerospace Exploration Agency, Institute of Aerospace Technology, Associate Senior Researcher, 総合技術研究本部空気力学研究グループ, 主任研究員 (90281584)
NAKAJIMA Hideki Kyushu University, Interdisciplinary Graduate School of Engineering Sciences, Professor, 総合理工学研究院, 教授 (60112306)
OTSU Hirotaka Shizuoka University, Faculty of Engineering, Research Associate, 工学部, 助手 (20313934)
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| Project Period (FY) |
2003 – 2005
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| Keywords | Plasma / Spacecraft / magnetohydrodynamics / Solar Wind / Magnetopause / Magneto-Plasma-Sail / 電磁プラズマセイル |
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| Research Abstract |
1.The thrust characteristics of the Magnetic Sail are quantitatively obtained by numerical simulations of MHD equations, which successfully revealed the momentum transferring process from the solar wind to the coil of the Magnetic Sail.
2.Interaction of the solar wind with the magnetic sail is numerically simulated by the full particle method. Fundamental features of the flow field and the induced electromagnetic field around the small magnetic sail are clarified. Force acting upon the magnetic sail is estimated.
3.Electromagnetic interaction between the solar wind and sub-scale magnetic sails was numerically analyzed to assess reaction forces on the magnetic sail. The hybrid particle-in-cell method was used. An approximate formula to compute the drag coefficient in a wide range of magnetic sail dimension has been developed.
4.In order to simulate the interaction between the solar wind and the artificially deployed magnetic field produced around a magnetic sail spacecraft, a laboratory simulator was designed and constructed inside the space chamber.
5.We find that for a spacecraft with a radius of 300m and a magnetic field of 0.02T, the Magneto Plasma Sail can achieve a thrust of 25N and a thrust to power ratio of 540mN/kW, which are much larger than those of ion thrusters.
6.The magnetic field inflation by the plasma injection is simulated in three-dimensional space using magnetohydrodynamics. The simulation results show that the ratio of the strength of inflated magnetic field to that of "original' (the initial magnetic field) depends neither on the ratio of the injected plasma dynamic pressure to the magnetic pressure nor on the dipole magnetic moment.
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Research Products
(47 results)
