2015 Fiscal Year Final Research Report
Research and Development of High-Total-Impulse Electrothermal Pulsed Plasma Thrusters for Powered Flight of Nano-Satellites
| Project/Area Number |
25289310
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| Research Category |
Grant-in-Aid for Scientific Research (B)
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| Allocation Type | Partial Multi-year Fund |
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| Section | 一般 |
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| Research Field |
Aerospace engineering
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| Research Institution | Osaka Institute of Technology |
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Principal Investigator |
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| Project Period (FY) |
2013-04-01 – 2016-03-31
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| Keywords | 宇宙推進 / 電気推進 / パルスプラズマスラスタ / 電熱加速 / 超小型衛星 / 動力飛行 / 大電力 / 高総力積 |
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| Outline of Final Research Achievements |
In micro/nano satellite R&D Projects, for example in the Project of Osaka Institute of Technology Electric-Rocket-Engine onboard Small Space Ship (PROITERES), the 2nd PROITERES nano-satellite with electric thrusters for powered flight has been developed. The main mission of the 2nd PROITERES is to change long-distance orbital altitude with electrothermal Pulsed Plasma Thrusters (PPTs). The PPT was developed by increasing electric power and designing Multi-Discharge-Room type PPT (MDR-PPT). The performance of the new high-power PPT is the maximum impulse bit of 2,415 μNs with a charging energy of 31.59 J. Furthermore, the PPT achieved successful operation of 100,000 shots using Power Processing Unit (PPU) engineering model.
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| Free Research Field |
電気推進
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