| Budget Amount *help |
¥16,120,000 (Direct Cost: ¥12,400,000、Indirect Cost: ¥3,720,000)
Fiscal Year 2017: ¥4,420,000 (Direct Cost: ¥3,400,000、Indirect Cost: ¥1,020,000)
Fiscal Year 2016: ¥6,370,000 (Direct Cost: ¥4,900,000、Indirect Cost: ¥1,470,000)
Fiscal Year 2015: ¥5,330,000 (Direct Cost: ¥4,100,000、Indirect Cost: ¥1,230,000)
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| Outline of Final Research Achievements |
We developed a new reconstruction technique titled nozzle-throat reconstruction technique to estimate nozzle-throat-erosion history and oxidizer-to-fuel-mass-ratio history in hybrid rockets. Static-firing tests were carried out on a 2kN-class hybrid-rocket motor under varying oxidizer-flowrates to evaluate the accuracy of reconstructed results. For equivalence ratios from 0.6 to 1.4, the relationship between nozzle-throat-erosion rate and equivalence ratio of reconstructed results displays a trend consistent with chemical-kinetic-limited heterogeneous-combustion theory, as well as predictions made by previous researchers. Also, we selected some materials which can prevent nozzle erosion and evaluated anti-erosion characteristics by combustion experiments. As an experimental result, graphite coated by silicon carbide showed good anti-erosion characteristics for hybrid rocket nozzles.
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