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自己加圧式ロケットエンジン用液体推進剤の流動特性に関する研究
https://doi.org/10.15118/00010392
https://doi.org/10.15118/00010392c67bd434-29f3-4c2c-9fd4-0ebf15a01990
名前 / ファイル | ライセンス | アクション |
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A467_summary (204.9 kB)
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A467 (19.4 MB)
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Item type | 学位論文 / Thesis or Dissertation(1) | |||||
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公開日 | 2021-06-23 | |||||
タイトル | ||||||
言語 | ja | |||||
タイトル | 自己加圧式ロケットエンジン用液体推進剤の流動特性に関する研究 | |||||
言語 | ||||||
言語 | jpn | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_db06 | |||||
資源タイプ | doctoral thesis | |||||
ID登録 | ||||||
ID登録 | 10.15118/00010392 | |||||
ID登録タイプ | JaLC | |||||
アクセス権 | ||||||
アクセス権 | open access | |||||
アクセス権URI | http://purl.org/coar/access_right/c_abf2 | |||||
著者 |
安田, 一貴
× 安田, 一貴 |
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抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 航空宇宙産業の発展に伴い,推進系の小型,軽量,簡素化が求められている.これらの需要に応える選択肢の一つに,亜酸化窒素の推進剤利用が挙げられる.亜酸化窒素は,常温で高い飽和蒸気圧を有することから,別途加圧システムを必要せず自己加圧供給が可能であるほか,常温で液体として取り扱うことができる.これらの特長により,打ち上げ用ロケットだけでなく,小型衛星のキックモータや姿勢制御用スラスタ,惑星着陸および帰還用ロケットへの適用も期待されている.一方で,自己加圧供給特有の課題も存在する.推進剤を自己加圧供給する場合,圧力低下による減圧沸騰やキャビテーションにより流れが混相化するため,圧力損失および流量予測が困難な点である.推進剤の流量はロケットエンジンの推進性能に直結するため,推進系の適切な設計や推力予測精度の向上には,推進剤流量の推定は極めて重要な要素である.本研究では,亜酸化窒素を用いた各種試験を実施し,実験的に得られた結果を多角的に評価することで,自己加圧式ロケットエンジンに伴う気液二相流の流動特性を解明することを目的としている.また,得られた知見から流量および推力の予測精度向上を図るものである.ここで対象とする流れ場は非定常性の強い気液二相流であり,温度や圧力のみで評価することは困難である.そこで,可視化した流路内を通過する気液二相流を高速撮影することで流動様式を評価し,壁面の気泡流速は 5-10 m/s 程度,気泡径は数 100 μm であることを明らかにした.また,新規に開発したボイド率計により気相と液相の割合を計測し,流動特性との相関を評価した結果から,ボイド率は 0.3-0.6 程度であり,供給に伴い次第に増加する傾向が明らかになった.また,ボイド率の増加に伴いインジェクタ流量係数は線形的に低下する傾向が示唆された.さらに,二相流 Re 数で摩擦損失係数を評価すると,単相流における同 Re 数における理論値に対して,最大で 2 倍程度になることを明らかにした.一方で,インジェクタ流量係数について,流体温度の上昇とともに流量係数も増加傾向にあることが明らかになった.亜酸化窒素の熱力学的効果パラメータは極めて高く,流体温度が高いほど,生成される気泡の体積抑制作用である熱力学的効果が顕著になったためと考えられる.また,インジェクタ下流圧が上流圧の半分程度以下である場合,インジェクタポート内で臨界二相流を形成することで流れがチョークするのに対し,比較的燃焼圧が高い(インジェクタレジスタンスが小さい)条件では供給系と燃焼の連成による燃焼振動が見られ,流量係数は流し試験にて取得した値よりも大きく見積もられる可能性が示唆された. | |||||
言語 | ja | |||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | With the development and progress within the aerospace industry, propulsion systems are required to be compact, lightweight, and simple. One solution to respond to these demands is using nitrous oxide as liquid propellant. Since nitrous oxide has a high saturated vapor pressure, it can be self-pressurized without an external pressurizing system and can also be handled as a liquid at normal temperature. Due to these advantages, it is expected to be used not only to launch rockets, but also to kick motors for small satellites, attitude control thrusters, planet landing, and return rockets. On the other hand, there are some problems specific to self- pressurization. With self-pressurization, it is difficult to predict the pressure loss and flow rate of the propellant because the gas-liquid two-phase flow is formed by flashing and cavitation caused by the pressure drop. Estimating the propellant mass flow rate is extremely important to accurately predict the thrust profile. In this study, the flow characteristics of gas-liquid two-phase with self-pressurization were evaluated by conducting various tests using nitrous oxide. The findings obtained in this study may contribute to improving the prediction accuracy of flow rate and thrust. The flow focused on in this study is a strongly unsteady gas-liquid two-phase flow, and it is not appropriate to evaluate the flow regime only by temperature and pressure. Therefore, the flow regime was evaluated by high- speed shooting of the gas-liquid two-phase flow passing through the visualized feed line. This method showed that the bubble flow velocity on the wall surface was about 5-10 m/s and the bubble diameter was several hundred μm. In addition, the results of measuring the ratio of gas and liquid phase with a newly developed void fraction meter suggest that the void fraction was about 0.3-0.6, and it gradually increased with supply. It was also found that the injector flow coefficient tended to decrease linearly as the void fraction increases. Furthermore, when the friction factor was evaluated by the two-phase flow Re number estimated from the obtained void ratio, it was about twice the theoretical value of the same Re number in the single-phase flow. On the other hand, it became clear that the injector flow coefficient tends to increase as the fluid temperature rises. The thermodynamic effect, which is the volume-suppressing effect of the bubbles generated, became remarkable as the fluid temperature increased. When the downstream pressure of the injector was less than half of the upstream pressure, the two-phase flow was choked at the injector port. The chamber pressure oscillation was observed due to the coupling of the supply system and combustion, suggesting that the injector flow coefficient may be larger than the value obtained in the cold flow tests. | |||||
言語 | en | |||||
学位授与機関 | ||||||
学位授与機関識別子Scheme | kakenhi | |||||
学位授与機関識別子 | 10103 | |||||
言語 | ja | |||||
学位授与機関名 | 室蘭工業大学 | |||||
言語 | en | |||||
学位授与機関名 | Muroran Institute of Technology | |||||
学位名 | ||||||
言語 | ja | |||||
学位名 | 博士(工学) | |||||
学位の種別 | ||||||
ja | ||||||
課程博士 | ||||||
学位授与番号 | ||||||
学位授与番号 | 甲第467号 | |||||
報告番号 | ||||||
ja | ||||||
甲第467号 | ||||||
学位記番号 | ||||||
ja | ||||||
博甲第467号 | ||||||
研究科・専攻 | ||||||
ja | ||||||
工学専攻 | ||||||
学位授与年月日 | ||||||
学位授与年月日 | 2021-03-23 | |||||
日本十進分類法 | ||||||
主題Scheme | NDC | |||||
主題 | 538 | |||||
著者版フラグ | ||||||
出版タイプ | VoR | |||||
出版タイプResource | http://purl.org/coar/version/c_970fb48d4fbd8a85 | |||||
フォーマット | ||||||
内容記述タイプ | Other | |||||
内容記述 | application/pdf |