Development and Verification of End-burning Type Hybrid Rockets Using Optical Modeling Technology
| Project/Area Number |
15K14243
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| Research Category |
Grant-in-Aid for Challenging Exploratory Research
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| Allocation Type | Multi-year Fund |
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| Research Field |
Aerospace engineering
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| Research Institution | Hokkaido University |
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Principal Investigator |
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| Project Period (FY) |
2015-04-01 – 2017-03-31
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| Project Status |
Completed (Fiscal Year 2016)
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| Budget Amount *help |
¥3,900,000 (Direct Cost: ¥3,000,000、Indirect Cost: ¥900,000)
Fiscal Year 2016: ¥1,690,000 (Direct Cost: ¥1,300,000、Indirect Cost: ¥390,000)
Fiscal Year 2015: ¥2,210,000 (Direct Cost: ¥1,700,000、Indirect Cost: ¥510,000)
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| Keywords | ハイブリッドロケット / 端面燃焼 / ロケット / 航空宇宙工学 / 燃焼 / 固体燃焼 |
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| Outline of Final Research Achievements |
The authors have previously proposed the concept of end burning type hybrid rockets which would use cylindrical fuel grains consisting of an array of many small ports running in the axial direction through which oxidizer gas would flow. Because of difficulty in manufacturing a fuel grain, the end burning hybrid rocket had yet to be achieved. The recent progress in 3D printing technology made novel end burning type hybrid rockets possible. The results of verification firing tests clearly distinguish the initial transient and steady periods of the end burning mode, and prove that no oxidizer to fuel ratio shift occurs during firing. Combustion experiments using single port fuel samples of 0.2 to 0.5 mm in inner diameter show that two combustion modes of flame propagating combustion and stabilized combustion are divided by a critical friction velocity and the flame traveling velocity in the stabilized mode coincides with the regression rate of the end-burning fuel.
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Report
(3 results)
Research Products
(13 results)
