|Budget Amount *help
¥46,280,000 (Direct Cost: ¥35,600,000、Indirect Cost: ¥10,680,000)
Fiscal Year 2015: ¥4,420,000 (Direct Cost: ¥3,400,000、Indirect Cost: ¥1,020,000)
Fiscal Year 2014: ¥10,530,000 (Direct Cost: ¥8,100,000、Indirect Cost: ¥2,430,000)
Fiscal Year 2013: ¥10,140,000 (Direct Cost: ¥7,800,000、Indirect Cost: ¥2,340,000)
Fiscal Year 2012: ¥21,190,000 (Direct Cost: ¥16,300,000、Indirect Cost: ¥4,890,000)
|Outline of Final Research Achievements
The spacecraft reentering into the atmosphere experiences a severe aerodynamic heating caused by the hot plasma flow around it. For flight safety, it is required to mitigate such a severe heating environment in addition to developing a heat protection system for the spacecraft. Because the hot plasma is influenced by the existence of the electromagnetic field, it is possible to make use of the electromagnetic force to mitigate such a severe heating environment. In this study, we investigated several problems inherent to this technique when it is applied to the spacecraft reentering to an atmospheric planet; ranging from the feasibility of the heat flux distribution control to the effect of high altitude flight.