2005 Fiscal Year Final Research Report Summary
Control of weakly ionized flow around a reentry vehicle and aerodynamic heating by means of electromagnetic effect
| Project/Area Number |
15206093
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| Research Category |
Grant-in-Aid for Scientific Research (A)
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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 |
ABE Takashi Japan Aerospace Exploration Agency, Institute of Space and Astronautical Science, Professor, 宇宙科学研究本部宇宙輸送工学研究系, 教授 (60114849)
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| Co-Investigator(Kenkyū-buntansha) |
FUNAKI Ikko Japan Aerospace Exploration Agency, Institute of Space and Astronautical Science, Asso.Professor, 宇宙科学研究本部宇宙輸送工学研究系, 助教授 (50311171)
OTSU Hirotaka Shizuoka University, Department of Engineering, Research Associate, 工学部, 助手 (20313934)
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| Project Period (FY) |
2003 – 2005
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| Keywords | Reentry vehicle / Weakly ionized flow / Magnetic effect |
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| Research Abstract |
The biggest challenge for a reentry vehicle from space is how to control the high temperature gas flow around the vehicle to prevent its heating-up. Traditionally, the control was passively managed by means of he heat protection system. On the contrary, we consider, in the present study, the active control by using the electro-magnetic effect and investigate its feasibility both experimentally and numerically. In the experiment, the flow behavior around the magnetized body set in the arc-jet wind tunnel was investigated. For this purpose, the translational temperature spatial distribution was measured by means of the absorption spectroscopy for which a new method was developed, which enables us to apply the absorption spectroscopy even in a strong magnetic field environment. The result shows the shock layer enhancement due to the magnetic field application, as the theory predicted. The present result gives a sound basis to develop the numerical analysis of the present phenomenon, and gives a significant contribution for the relevant investigation.
The numerical simulation was developed for the present electromagnetic effect. The simulation result which shows a reasonable agreement with the present experimental result. It was found though the numerical simulation that the vehicle surface has a significant effect on the elelectromagnetic effect, which was experimentally confirmed. It is also confirmed that the electomagnetic effect is effective in a flight condition. In addition, the feasibility of the flight demonstration of the present method was revealed.
The present study clarified the basic phenomenon of the electromagenetic effect and its feasibility of the application to the reentry vehicle.
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