| Budget Amount *help |
¥19,890,000 (Direct Cost: ¥15,300,000、Indirect Cost: ¥4,590,000)
Fiscal Year 2012: ¥4,290,000 (Direct Cost: ¥3,300,000、Indirect Cost: ¥990,000)
Fiscal Year 2011: ¥8,840,000 (Direct Cost: ¥6,800,000、Indirect Cost: ¥2,040,000)
Fiscal Year 2010: ¥6,760,000 (Direct Cost: ¥5,200,000、Indirect Cost: ¥1,560,000)
|
|---|
| Research Abstract |
These days, small satellites (less than 100 kg) are innovating the space utilization and development and one of the key technologies is the development of high-performance, small propulsion system using ion thrusters. The purpose of this study is to realize such advanced small propulsion systems and various subjects were conducted to understand the microwave discharge plasma (microwave transmission and plasma density profile), to clarify the characteristics of the thruster (plume, thrust, and thrust noise), and to verify the propulsion system (long time operation and BBM of gas system). The conclusions of these studies were utilized to design and develop the MIPS (miniature ion propulsion system) which was installed on a 50-kg, small satellite, Hodoyoshi-4.
|
