貯蔵性推進薬2液式アポジエンジンのポップ試験

• Material Type: 文書・図像類
• Title: 貯蔵性推進薬2液式アポジエンジンのポップ試験
• Author/Editor: 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
• Author Heading: 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
• Publication, Distribution, etc.: 航空宇宙技術研究所
• Publication Date: 1994-10
• Publication Date (W3CDTF): 1994-10
• Alternative Title: Pop tests of storable bipropellant liquid apogee engine
• Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory
• No. or year of volume/issue: 1253
• Volume: 1253
• Pages: 1-15
• ISSN (Periodical Title): ISSN : 0389-4010
• Text Language Code: jpn
• Subject Heading: 貯蔵性推進薬; 2液式アポジエンジン; ポップ試験; 静止技術試験衛星7; ETS-7; ヒドラジン; 4酸化2窒素; アポジ推進; 振動燃焼; 燃焼圧力; 噴流速度; レイノズル数; グラファイトノズル; 多素子噴射器; storable propellant; bipropellant liquid apogee engine; pop test; geostationary engineering test satellite 6; ETS 6; hydrazine; nitrogen tetroxide; apogee propulsion; vibration combustion; combustion pressure; injection speed; Reynolds number; graphite nozzle; multielement injector
• Target Audience: 一般
• Note (General): 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。; 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.; 資料番号: AA0004260000; レポート番号: NAL TR-1253
• Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=41229&item_no=1&attribute_id=31&file_no=1
• Access Restrictions: 限定公開
• Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）; https://irdb.nii.ac.jp
• Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ