軌道変換用OMSサブスケールエンジンの耐久性試験

• Material Type: 文書・図像類
• Title: 軌道変換用OMSサブスケールエンジンの耐久性試験
• Author/Editor: 黒田, 行郎; 只野, 真; 佐藤, 政裕; 日下, 和夫; 毛呂, 明夫; 青木, 由雄; 三木, 陽一郎; Kuroda, Yukio; Tadano, Makoto; Sato, Masahiro; Kusaka, Kazuo; Moro, Akio; Aoki, Yoshio; Miki, Yoichiro
• Author Heading: 黒田, 行郎; 只野, 真; 佐藤, 政裕; 日下, 和夫; 毛呂, 明夫; 青木, 由雄; 三木, 陽一郎; Kuroda, Yukio; Tadano, Makoto; Sato, Masahiro; Kusaka, Kazuo; Moro, Akio; Aoki, Yoshio; Miki, Yoichiro
• Publication, Distribution, etc.: 航空宇宙技術研究所
• Publication Date: 1996-06
• Publication Date (W3CDTF): 1996-06
• Alternative Title: Durability tests of OMS subscale engine for H-2 orbiting plane
• 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: 1294
• Volume: 1294
• Pages: 1-27
• ISSN (Periodical Title): ISSN : 0389-4010
• Text Language Code: jpn
• Subject Heading: 再使用型ロケットエンジン; 推進薬; 軌道変換; OMS; ZrO2/Ni燃焼器; 耐久性試験; セラミック被覆; 傾斜機能材料; FGM; セラミック金属接合; 燃焼器損傷評価; サブスケールエンジン; HOPE-2; 宇宙往還機; 2液式エンジン; reusable rocket engine; propellant; orbital transfer; ZrO2 Ni chamber; durability test; ceramic coating; functionally graded material; ceramic metal bonding; chamber damage evaluation; subscale engine; HOPE 2; reentry vehicle; bipropellant engine
• Target Audience: 一般
• Note (General): 将来の宇宙往還機に対応する再使用型高性能2液式エンジンの要求に応える為、金属とセラミックスの異種材料の組成を変化させた材料を1部に用いた燃焼器を製作し、エンジンの高性能化のためフィルム冷却率を0パーセントにした噴射器を用いて推力1200N級のNTO(4酸化2窒素)/MMH(メチルヒドラジン)を推進薬とする再生冷却式サブスケールエンジンの耐久性試験を行った。耐久性試験に先立って長秒時試験を行いエンジンの熱特性を調べた。また、燃焼器の損傷評価に用いたレプリカ試験法は燃焼器の損傷を推定するには有効であることを確認した。ここで行った試験結果は、現在計画されている完全傾斜機能化した(燃焼器部材の加熱部から冷却部までの全てが傾斜機能材料で構成されている場合を、完全傾斜機能化した燃焼器と称す)ZrO2溶射/Ni電鋳燃焼器の製作に必要な基礎データとするものである。; The reusable regeneratively cooled thrust engine, powered by Nitrogen Tetroxide (NTO)/Monomethyl Hydrazine (MMH) propellant, is a candidate for the Japanese Orbital Maneuvering System (OMS) engine. To improve engine performance, the current generation of this kind of reusable rocket engine is designed to operate with a minimum amount of cooling. Its high performance thrust chamber, however, coupled with extended reuse requirements imposes difficult cooling requirements, particularly in the throat region. To meet the cooling and life enhancement requirements, the inner wall of the thrust chamber incorporates a thermal barrier, such as a ceramic coating to reduce the large wall temperature difference. Such ceramic coatings on the wall of rocket thrust chambers have been employed for many years. However, the main drawback to the use of these ceramic coatings are the delamination between the ceramic side on the hot-gas wall and metal side on the cooling wall, and spalling or eventually flake-off during repeated thermal heat load in the combustion test. This is due to the large difference in the thermal coefficient of expansion between the ceramic coating and metal wall, and also to the low ductility of the ceramic coating. One promising method of improving adhesion of the ceramic coating to the metal wall in the thrust chamber is to apply Functionally Graded Materials (FGM) composed of ZrO2 and nickel which can withstand the lower thermal expansion of the ZrO2 thermal barrier coating and which is characterized by high thermal conductivity. For the past five years, the thermal fatigue properties of FGM specimens with a diameter of 30 mm have been examined by exposing them to the combustion gases of NTO/MMH propellant. The results of the heat cycle tests revealed improvement of ceramic-metal bonding. The FGM chamber employed in these tests consists of both ZrO2 and Ni components with sequential variation of characteristics from one side composed of ZrO2 to the other side composed of nickel. In this study, durability tests of a regeneratively cooled 1,200 N thrust engine composed of ZrO2/Ni FGM were conducted with NTO/MMH propellant. The film cooling fraction was reduced to zero percent of the total fuel flow rate to obtain high performance. A total of 260 firing tests were performed to evaluate the performance of the engine and to obtain thermal data, and also to inspect the thermal barrier coatings after the cycle of tests in this series.; 資料番号: AA0000557000; レポート番号: NAL TR-1294
• 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