2018 Fiscal Year Final Research Report
Downsizing of efficient bi-propellant rocket engine by using detonation combustion
| Project/Area Number |
17H06741
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| Research Category |
Grant-in-Aid for Research Activity Start-up
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| Allocation Type | Single-year Grants |
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| Research Field |
Aerospace engineering
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| Research Institution | Nagoya University |
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Principal Investigator |
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| Project Period (FY) |
2017-08-25 – 2019-03-31
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| Keywords | デトネーション / 航空宇宙推進工学 / 回転デトネーションエンジン |
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| Outline of Final Research Achievements |
This study aimed to downsize bi-propellant rocket engines by utilizing detonation combustion characterized by significantly fast combustion completion. In rotating detonation engines (RDEs), which are a type of rocket engines utilizing the detonation combustion, the combustors typically had annular configurations and consisted of two coaxial cylinders to stabilize detonation waves within the combustor. However, through investigation of the effects of combustor sizes on the engine performance, it has been revealed that a simple cylindrical configuration, in which the combustor consists only of one cylinder, can exert equivalent engine performances to conventional annular combustors by setting the propellant flow rate appropriately for the combustor cross-sectional area.
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| Free Research Field |
デトネーション工学
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| Academic Significance and Societal Importance of the Research Achievements |
本研究で単円筒RDEが二重円筒RDEに匹敵する性能を発揮しうることが明らかとなったことから，RDEの更なる小型化が可能となる．単円筒構造は，燃焼器の熱設計の観点からも簡素なシステムの成立につながり，有用である．翻って宇宙推進工学の観点からは，従来実現が難しかった比推力性能の高い超小型ロケットエンジンへの端緒が開かれた点で学術的・社会的に意義深い．本研究を更に発展させることで，燃焼器のクラスタ化によるコスト低減や単機での小型衛星搭載による機動性向上に資することが期待される．
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