Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
National Space Development Agency of Japan(NASDA)
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
航空宇宙技術研究所報告
雑誌名(英)
Technical Report of National Aerospace Laboratory TR-1053
巻
1053
ページ
16
発行年
1990-02
抄録（英）
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.
Specific Impulse Comparison of High Density Hydrocarbon Fuel Burned with Oxygen
naltr01053.pdf
(1.61MB)
