2026-03-06T11:40:18Z https://jaxa.repo.nii.ac.jp/oai

oai:jaxa.repo.nii.ac.jp:00044890 2023-06-20T21:49:02Z 1887:1893 1896:1898:1913:1917

High Performance Propellant Study-Oxygen Lithium Hydrogen Tripropellant- 高性能推進薬の研究-酵素・リチウム・水素プロペラント- 毛呂, 明夫 鈴木, 和雄 MORO, Akio SUZUKI, Kazuo The performance potential of the 02/Li/H2 tripropellant combination is among the highest available from chemical propellants. Theoretical performance calculations were made for L-02/L-Li in the mixture ratio range of 0.6 to 3.0 at the chamber pressure of 5 to 50 atm, with liquid hydrogen addition ranging from 0 to 35 percent of the total propellant flowrate. Results of the computations are presented in a series of curves, which show the variations in an important performance parameter (Isp, cf, C, etc) including proportions of hydrogen, mixture ratio, chamber pressure, and nozzle expansion area ratios. An experimental was performed to investigate the feasibility of the 02/Li/H2 tripropellant combination. The experimental firing results are presented in curves, which show the variations of characteristic exhaust velocity efficiencies taking into consideration the factors, such as lithium weight ratios, chamber length, lithium injection angles, and gas generator mixture ratios. Uncorrected characteristic velocity efficiencies were 80 to 88 percent, showing that the use of this tripropellant combination is feasible. 資料番号: NALTR0635000 レポート番号: NAL TR-635 航空宇宙技術研究所 National Aerospace Laboratory(NAL) 1980-10 eng technical report https://jaxa.repo.nii.ac.jp/records/44890 0389-4010 航空宇宙技術研究所報告 Technical Report of National Aerospace Laboratory TR-635 635 26 https://jaxa.repo.nii.ac.jp/record/44890/files/naltr00635.pdf application/pdf 3.3 MB 2020-01-29