低推力貯蔵性推進薬エンジンの高空性能

Material type: 文書・図像類

Author: 日下, 和夫ほか

Publisher: 航空宇宙技術研究所

Publication date: 1985-02

Material Format: Digital

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Note (General)：: High altitude simulation tests of a storable engine with a thrust of 500 N and a chamber pressure of 700 kpa were conducted to evaluate the nozzle per...

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Material Type: 文書・図像類
Title: 低推力貯蔵性推進薬エンジンの高空性能
Author/Editor: 日下, 和夫
黒田, 行郎
佐藤, 政裕
只野, 真
飯原, 重保
KUSAKA, Kazuo
KURODA, Yukio
SATO, Masahiro
TADANO, Makoto
IIHARA, Shigeyasu
Author Heading: 日下, 和夫
黒田, 行郎
佐藤, 政裕
只野, 真
飯原, 重保
KUSAKA, Kazuo
KURODA, Yukio
SATO, Masahiro
TADANO, Makoto
IIHARA, Shigeyasu
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1985-02
Publication Date (W3CDTF): 1985-02
Alternative Title: Performance of A Low Thrust Storable Engine With Large Area Ratio Nozzles
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-853
No. or year of volume/issue: 853
Volume: 853
Pages: 22-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: jpn
Target Audience: 一般
Note (General): High altitude simulation tests of a storable engine with a thrust of 500 N and a chamber pressure of 700 kpa were conducted to evaluate the nozzle performance at low thrust and low chamber pressure. Since the available facility did not allow tests of such an engine, an auxiliary annular ejector/diffuser system was developed. Two injectors, one with 15％ fuel film cooling and the other 25％, were used. A comparison of performances between nitrogen tetroxide/monomethyl hydrazine (NTO/MMH) and nitrogen tetroxide/hydrazine propellant systems was made. A vacuum specific impulse of 305 seconds was obtained with NTO/MMH and a 150:1 area ratio nozzle at a energy release efficiency of 95％. By altering fuel from MMH to hydrazine, a peak specific impulse of 317 seconds was measured with 25％ film cooling and a 150:1 nozzle. Large area ratio specific impulses can be predicted generally within 0.5％ when energy release efficiencies are evaluated from sea level thrust measurements with a low area ratio nozzle.
資料番号: NALTR0853000
レポート番号: NAL TR-853
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