Numerical anaysis of auto-ignition and flame structures of hypergolic liquid propellants by applying detailed chemical reaction models
| Project/Area Number |
26820379
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| Research Category |
Grant-in-Aid for Young Scientists (B)
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| Allocation Type | Multi-year Fund |
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| Research Field |
Aerospace engineering
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| Research Institution | Japan Aerospace EXploration Agency |
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Principal Investigator |
Tani Hiroumi 国立研究開発法人宇宙航空研究開発機構, 研究開発部門, 研究開発員 (80633784)
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| Project Period (FY) |
2014-04-01 – 2018-03-31
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| Project Status |
Completed (Fiscal Year 2017)
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| Budget Amount *help |
¥4,030,000 (Direct Cost: ¥3,100,000、Indirect Cost: ¥930,000)
Fiscal Year 2016: ¥1,040,000 (Direct Cost: ¥800,000、Indirect Cost: ¥240,000)
Fiscal Year 2015: ¥1,040,000 (Direct Cost: ¥800,000、Indirect Cost: ¥240,000)
Fiscal Year 2014: ¥1,950,000 (Direct Cost: ¥1,500,000、Indirect Cost: ¥450,000)
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| Keywords | 自燃性 / 自着火 / 噴霧燃焼 / 詳細化学反応 / 宇宙推進 / 数値流体力学 / 自燃性推進剤 / 着火遅れ時間 / 大規模詳細反応機構 / 数値解析 / 混相流 / 化学推進 / 液滴燃焼 |
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| Outline of Final Research Achievements |
Auto-ignition and spray combustion processes of hypergolic propellants used for spacecraft chemical propulsion were investigated to enhance the accuracy of the performance prediction of chemical thrusters. In experiments, we succeeded in acquiring images of auto-ignition processes of monomethlyhydrazine and nitrogen tetroxide, which were consist of the break of a liquid fan, vapor generation, gas ignition, and flame propagation. To simulate these processes, numerical simulation codes were constructed by applying detailed chemical reaction models. Simulations of spray combustion by using a lagrangian-model revealed that the combustion efficiency of the hydrazine spray is very sensitive to the droplet size. Furthermore, simulations with an interface tracking method suggested that the hydrogen abstraction reactions happening between the propellant vapor and ambient gases released a high heat such that the auto-ignition occurred near the liquid surfaces.
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Report
(5 results)
Research Products
(19 results)
