Specific Impulse Comparison of High Density Hydrocarbon Fuel Burned with Oxygen

Material type: 文書・図像類

Author: 熊谷, 達夫ほか

Publisher: 航空宇宙技術研究所

Publication date: 1990-02

Material Format: Digital

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Note (General)：: Performance tests of high density hydrocarbon fuel were conducted with a small rocket engine. The densities of the fuel examined, RJ-1J, HDF-1, and HD...

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Material Type: 文書・図像類
Title: Specific Impulse Comparison of High Density Hydrocarbon Fuel Burned with Oxygen
Author/Editor: 熊谷, 達夫
植田, 修一
佐藤, 政裕
須藤, 孝幸
宮島, 博
渡辺, 篤太郎
山川, 正紀
KUMAGAI, Tatsuo
UEDA, Shuichi
SATO, Masahiro
SUDO, Takayuki
MIYAJIMA, Hiroshi
WATANABE, Atsutaro
YAMAKAWA, Masanori
Author Heading: 熊谷, 達夫
植田, 修一
佐藤, 政裕
須藤, 孝幸
宮島, 博
渡辺, 篤太郎
山川, 正紀
KUMAGAI, Tatsuo
UEDA, Shuichi
SATO, Masahiro
SUDO, Takayuki
MIYAJIMA, Hiroshi
WATANABE, Atsutaro
YAMAKAWA, Masanori
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1990-02
Publication Date (W3CDTF): 1990-02
Alternative Title: 高密度炭化水素燃料/酸素の比推力性能の相対比較
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-1053
No. or year of volume/issue: 1053
Volume: 1053
Pages: 16-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: eng
Target Audience: 一般
Note (General): Performance tests of high density hydrocarbon fuel were conducted with a small rocket engine. The densities of the fuel examined, RJ-1J, HDF-1, and HDF-3 were 0.851, 0.996, and 1.006 respectively. The RJ-1J, which is used for the Japanese H-1 rocket, served as a reference for comparison. The thrust of the rocket engine was 490N at a chamber pressure of 2.94 MPa and a nozzle area ratio of 5:1. The thrust chamber was water cooled, and gaseous oxygen was used as the oxidizer. To simulate a duel fuel condition, a small amount of gaseous hydrogen(2％ of hydrocarbon fuel) was added to the combustion chamber. The effect of the amount of hydrogen addition on specific impulse was also tested. Measured peak vacuum specific impulses for RJ-1J, HDF-1, and HDF-3 respectively were 291, 290, and 287s, which is in qualitative accord with theoretical prediction. Specific impulse increased with the amount of hydrogen added as predicted. However, energy release efficiency was not affected appreciably, since it was very near to 100％ at the conditions tested. It was concluded that two kinds of high density fuel tested have acceptable performances and properties for dual fuel engines. An engine specific impulse may be extrapolated from the present experiment to be 345 s at a 1000kN thrust and 10 MPa chamber pressure level.
資料番号: NALTR1053000
レポート番号: NAL TR-1053
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45312&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45312&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