RESEARCH ON ENHANCEMENT OF IMPULSE FOR ELECTROTHERMAL PULSED PLASMA THRUSTERS ONBOARD SMALL SATELLITES
| Project/Area Number |
19360382
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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 | Osaka Institute of Technology |
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Principal Investigator |
TAHARA Hirokazu Osaka Institute of Technology, 工学部, 教授 (20207210)
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| Project Period (FY) |
2007 – 2009
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| Project Status |
Completed (Fiscal Year 2009)
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| Budget Amount *help |
¥19,110,000 (Direct Cost: ¥14,700,000、Indirect Cost: ¥4,410,000)
Fiscal Year 2009: ¥6,500,000 (Direct Cost: ¥5,000,000、Indirect Cost: ¥1,500,000)
Fiscal Year 2008: ¥6,370,000 (Direct Cost: ¥4,900,000、Indirect Cost: ¥1,470,000)
Fiscal Year 2007: ¥6,240,000 (Direct Cost: ¥4,800,000、Indirect Cost: ¥1,440,000)
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| Keywords | 電気推進 / 航空宇宙流体・構造・航法・制御・推進 / パルスプラズマスラスタ / 高インパルスビット / 超小型人工衛星 / テフロン / 電熱加速 / 推進性能 / 流れ場計算 / 設計相似則 / 小型人工衛星 |
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| Research Abstract |
Electrothermal PPT has been studied in order to understand physical phenomena and improve thrust performances with both experiments and numerical simulations. The length and diameter of a Teflon discharge room of electrothermal PPTs are changed to find the optimum configuration of PPT heads in very low energy operations for the satellite. Initial impulse bit measurements are conducted, and long operations and endurance tests are also carried out with the optimum PPT configuration. The PPT was operated with a small stored energy of 2.43J per shot. The PPT with a discharge room diameter of 1.0mm and an insulator length of 9.0mm stably generated the highest impulse bit of 250μNs with the highest thrust efficiency of 18%. In the endurance test, the total impulse of about 5Ns, as shown in Fig.2, was achieved in 53,000-shot operation with 2.43J/shot. Finally, the engineering model of PPT system was developed.
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Report
(4 results)
Research Products
(24 results)
