Aug, 2017 - Mar, 2019
Downsizing of efficient bi-propellant rocket engine by using detonation combustion
Japan Society for the Promotion of Science Grants-in-Aid for Scientific Research Grant-in-Aid for Research Activity Start-up
- Grant number
- 17H06741
- Japan Grant Number (JGN)
- JP17H06741
- Authorship
- Principal investigator
- Grant amount
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- (Total)
- 2,860,000 Japanese Yen
- (Direct funding)
- 2,200,000 Japanese Yen
- (Indirect funding)
- 660,000 Japanese Yen
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.
- Link information
- ID information
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- Grant number : 17H06741
- Japan Grant Number (JGN) : JP17H06741