| Budget Amount *help |
¥4,810,000 (Direct Cost: ¥3,700,000、Indirect Cost: ¥1,110,000)
Fiscal Year 2018: ¥1,430,000 (Direct Cost: ¥1,100,000、Indirect Cost: ¥330,000)
Fiscal Year 2017: ¥1,950,000 (Direct Cost: ¥1,500,000、Indirect Cost: ¥450,000)
Fiscal Year 2016: ¥1,430,000 (Direct Cost: ¥1,100,000、Indirect Cost: ¥330,000)
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| Outline of Final Research Achievements |
A swirling-injection end-burning method was proposed to attain high fuel regression rate and constant O/F burning for hybrid rocket engines. The burning behavior and engine performance using low melting temperature fuels such as paraffin-WAX and LT were investigated. The influencing parameters on fuel regression rate were clarified, and the empirical regression rate correlation was obtained for engine design and performance prediction. The engine demonstrated the regression rate of around 5 mm/s for WAX/GOX, whereas the value considerably decreased for WAX/LOX and WAX showed some cracks owing to cryogenic LOX temperature. The LT fuel showed lower regression rate than WAX fuel, however burning of LT/LOX was stable without fuel crack. To increase the regression rate of LT fuel, increasing the swirl strength is considered to be effective. It was found that the O/F ratio varied with time.
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