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One of the problems encountered during the development of the engine was the occurrence of pops (popping) at the higher operating chamber pressures. Pops are irregular high amplitude pressure pulses. It is generally agreed that pops is a liquid spray/gas two-phase explosion triggered by a local explosion near the jet impingement region. The effects of operating parameters on pops observed in the development tests of the apogee engine for the ETS-6 were inconsistent with those reported earlier for single impingelement injectors: pops with the apogee engine injectors was more likely to occur at higher chamber pressures, higher injection velocities, and higher propellant temperatures. Pops data were correlated fairly well in chamber pressures (bar-P(sub c)) vs. fuel Reynolds number (R(sub ef)) plane. However, the range of operating parameters for the above correlation were very narrow since they were obtained during injector screening tests for a particular application to the apogee engine. It was also felt that the above correlation was too simplistic to capture any effect of design parameters of multi-element injectors. In the present study, the demarcation between pops and the pops-free region was determined in broader operating ranges and design parameters. The range of bar-P(sub c) and R(sub ef) was extended by exchanging graphite nozzle throat inserts with different throat diameters. The injectors were carefully selected to obtain effects, if any, of: (1) film cooling fraction; (2) secondary mixing; and (3) number of elements and/or fuel orifice diameters. It was found that there was a threshold fuel Reynolds number below which no pops were observed at any chamber pressures and that the pops region curve in the bar-P(sub c)-R(sub ef) plane had two branches: upper branches and lower branches.", "subitem_description_type": "Other"}]}, "item_3_description_32": {"attribute_name": "資料番号", "attribute_value_mlt": [{"subitem_description": "資料番号: AA0004260000", "subitem_description_type": "Other"}]}, "item_3_description_33": {"attribute_name": "レポート番号", "attribute_value_mlt": [{"subitem_description": "レポート番号: NAL TR-1253", "subitem_description_type": "Other"}]}, "item_3_publisher_8": {"attribute_name": "出版者", "attribute_value_mlt": [{"subitem_publisher": "航空宇宙技術研究所"}]}, "item_3_publisher_9": {"attribute_name": "出版者(英)", "attribute_value_mlt": [{"subitem_publisher": "National Aerospace Laboratory (NAL)"}]}, "item_3_source_id_21": {"attribute_name": "ISSN", "attribute_value_mlt": [{"subitem_source_identifier": "0389-4010", "subitem_source_identifier_type": "ISSN"}]}, "item_3_text_35": {"attribute_name": "JAXAカテゴリ", "attribute_value_mlt": [{"subitem_text_value": "JAXAカテゴリ: 航空宇宙技術研究所"}]}, "item_3_text_36": {"attribute_name": "JAXAカテゴリ2", "attribute_value_mlt": [{"subitem_text_value": "JAXAカテゴリ2: AP"}]}, "item_3_text_43": {"attribute_name": "DSpaceコレクション番号", "attribute_value_mlt": [{"subitem_text_value": "DSpaceコレクション番号: 7"}]}, "item_3_text_6": {"attribute_name": "著者所属", "attribute_value_mlt": [{"subitem_text_value": "航空宇宙技術研究所 角田宇宙推進技術研究センター"}, {"subitem_text_value": "航空宇宙技術研究所 角田宇宙推進技術研究センター"}, {"subitem_text_value": "航空宇宙技術研究所 角田宇宙推進技術研究センター"}, {"subitem_text_value": "航空宇宙技術研究所 角田宇宙推進技術研究センター"}, {"subitem_text_value": "宇宙開発事業団"}, {"subitem_text_value": "石川島播磨重工業"}, {"subitem_text_value": "石川島播磨重工業"}]}, "item_3_text_7": {"attribute_name": "著者所属(英)", "attribute_value_mlt": [{"subitem_text_language": "en", "subitem_text_value": "National Aerospace Laboratory Kakuda Research Center"}, 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[{"creatorName": "Sato, Masahiro", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "451323", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Kusaka, Kazuo", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "451324", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Kobayashi, Hideyuki", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "451325", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Iihara, Sigeyasu", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "451326", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Ban, Hiroyuki", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "451327", "nameIdentifierScheme": "WEKO"}]}]}, "item_files": {"attribute_name": "ファイル情報", "attribute_type": "file", "attribute_value_mlt": [{"accessrole": "open_date", "date": [{"dateType": "Available", "dateValue": "2020-01-27"}], 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"subitem_subject_scheme": "Other"}, {"subitem_subject": "hydrazine", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "nitrogen tetroxide", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "apogee propulsion", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "vibration combustion", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "combustion pressure", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "injection speed", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "Reynolds number", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "graphite nozzle", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "multielement injector", "subitem_subject_language": "en", 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貯蔵性推進薬2液式アポジエンジンのポップ試験
https://jaxa.repo.nii.ac.jp/records/41229
https://jaxa.repo.nii.ac.jp/records/412292f44e4e8-d0a0-4e9c-b480-1a42c2f78e31
名前 / ファイル | ライセンス | アクション |
---|---|---|
naltr01253.pdf (2.0 MB)
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Item type | テクニカルレポート / Technical Report(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 貯蔵性推進薬2液式アポジエンジンのポップ試験 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 貯蔵性推進薬 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 2液式アポジエンジン | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ポップ試験 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 静止技術試験衛星7 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ETS-7 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ヒドラジン | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 4酸化2窒素 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | アポジ推進 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 振動燃焼 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 燃焼圧力 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 噴流速度 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | レイノズル数 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | グラファイトノズル | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 多素子噴射器 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | storable propellant | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | bipropellant liquid apogee engine | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pop test | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | geostationary engineering test satellite 6 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | ETS 6 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | hydrazine | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | nitrogen tetroxide | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | apogee propulsion | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | vibration combustion | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | combustion pressure | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | injection speed | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Reynolds number | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | graphite nozzle | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | multielement injector | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_18gh | |||||
資源タイプ | technical report | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Pop tests of storable bipropellant liquid apogee engine | |||||
著者 |
黒田, 行郎
× 黒田, 行郎× 只野, 真× 佐藤, 政裕× 日下, 和夫× 小林, 秀之× 飯原, 重保× 伴, 浩之× Kuroda, Yukio× Tadano, Makoto× Sato, Masahiro× Kusaka, Kazuo× Kobayashi, Hideyuki× Iihara, Sigeyasu× Ban, Hiroyuki |
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著者所属 | ||||||
航空宇宙技術研究所 角田宇宙推進技術研究センター | ||||||
著者所属 | ||||||
航空宇宙技術研究所 角田宇宙推進技術研究センター | ||||||
著者所属 | ||||||
航空宇宙技術研究所 角田宇宙推進技術研究センター | ||||||
著者所属 | ||||||
航空宇宙技術研究所 角田宇宙推進技術研究センター | ||||||
著者所属 | ||||||
宇宙開発事業団 | ||||||
著者所属 | ||||||
石川島播磨重工業 | ||||||
著者所属 | ||||||
石川島播磨重工業 | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Kakuda Research Center | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Kakuda Research Center | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Kakuda Research Center | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Kakuda Research Center | ||||||
著者所属(英) | ||||||
en | ||||||
National Space Development Agency of Japan | ||||||
著者所属(英) | ||||||
en | ||||||
Ishikawajima-Harima Heavy Industries Co, Ltd | ||||||
著者所属(英) | ||||||
en | ||||||
Ishikawajima-Harima Heavy Industries Co, Ltd | ||||||
出版者 | ||||||
出版者 | 航空宇宙技術研究所 | |||||
出版者(英) | ||||||
出版者 | National Aerospace Laboratory (NAL) | |||||
書誌情報 |
航空宇宙技術研究所報告 en : Technical Report of National Aerospace Laboratory 巻 1253, p. 1-15, 発行日 1994-10 |
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抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 軌道上重量2トン級の静止技術試験衛星ETS-6型には、加圧供給方式の推進薬ヒドラジン(N2H4)/4酸化2窒素(NTO)を用いたアポジ推進システムが用いられた。本推進薬を用いたアポジエンジンの開発試験の過程で高燃焼圧側において高振幅の振動燃焼(以下、ポップまたはポッピングと称す)が発生した。開発試験で生じたポップの結果では燃焼圧力が高く、推進薬の噴流速度が大で推進薬温度が高い場合にポップが生じやすく、これまでに報告された条件とは必ずしも一致しないことが示された。そのため、試験結果と合致するパラメータとして燃焼圧Pcと燃料噴流の基準レイノルズ数Refの相関を行った。開発試験の結果では、Pc‐Refの狭い範囲について関係付けたのでRefの範囲を拡げてPc‐Refの相関を詳しく調べた。試験では、燃焼圧と燃料噴流の基準レイノルズ数を独立に変えて試験出来るようにスロート部はスロート径の異なるグラファイトノズル数種を挿入する方式とした。ポップ試験に用いた噴射器は、開発試験で使用された噴射器の中から、(1)フィルム冷却率、(2)燃料噴流の2次混合の効果、(3)噴射エレメント数の影響を調べるために選定したものである。試験結果では、ポップ発生限界はPc‐Ref平面で半島状の囲まれた領域内にあり、従来考えられていたよりも複雑であることが確認された。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | A pressure-fed, blowdown, Hydrazine/NTO (Nitrogen Tetroxide) apogee propulsion system had been selected for the ETS-6. One of the problems encountered during the development of the engine was the occurrence of pops (popping) at the higher operating chamber pressures. Pops are irregular high amplitude pressure pulses. It is generally agreed that pops is a liquid spray/gas two-phase explosion triggered by a local explosion near the jet impingement region. The effects of operating parameters on pops observed in the development tests of the apogee engine for the ETS-6 were inconsistent with those reported earlier for single impingelement injectors: pops with the apogee engine injectors was more likely to occur at higher chamber pressures, higher injection velocities, and higher propellant temperatures. Pops data were correlated fairly well in chamber pressures (bar-P(sub c)) vs. fuel Reynolds number (R(sub ef)) plane. However, the range of operating parameters for the above correlation were very narrow since they were obtained during injector screening tests for a particular application to the apogee engine. It was also felt that the above correlation was too simplistic to capture any effect of design parameters of multi-element injectors. In the present study, the demarcation between pops and the pops-free region was determined in broader operating ranges and design parameters. The range of bar-P(sub c) and R(sub ef) was extended by exchanging graphite nozzle throat inserts with different throat diameters. The injectors were carefully selected to obtain effects, if any, of: (1) film cooling fraction; (2) secondary mixing; and (3) number of elements and/or fuel orifice diameters. It was found that there was a threshold fuel Reynolds number below which no pops were observed at any chamber pressures and that the pops region curve in the bar-P(sub c)-R(sub ef) plane had two branches: upper branches and lower branches. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0389-4010 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0004260000 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: NAL TR-1253 |