タイトル（掲載誌）航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-1053
一般注記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
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45312&item_no=1&attribute_id=31&file_no=1
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース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