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Other TitleChemical kinetics evaluation of ionic liquid propellant composition
Author(jpn)伊東山, 登; 伊里, 友一朗; 三宅, 淳巳; 羽生, 宏人
Author(eng)Itouyama, Noboru; Izato, Yuichiro; Miyake, Atsumi; Habu, Hiroto
Author Affiliation(jpn)東京大学; 横浜国立大学; 横浜国立大学; 宇宙航空研究開発機構宇宙科学研究所宇宙飛翔工学研究系(JAXA)(ISAS)
Author Affiliation(eng)The University of Tokyo; Yokohama National University; Yokohama National University; Department of Space Flight Systems, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)
Issue Date2018-01-10
Japan Aerospace Exploration Agency (JAXA)
Publication title宇宙航空研究開発機構研究開発報告: 高エネルギー物質研究会: 平成29年度研究成果報告書
JAXA Research and Development Report: Technical Report of The Research Activity for High Energy Materials (2017)
Start page27
End page33
Publication date2018-01-10
Abstract既往の研究よりアンモニウムジニトラミドを基材とし, 燃料2 種と融点降下剤2 種の計4個の組み合わせで液化可能であることが分かっている. NASA-CEA をはじめとする平衡論的計算により比推力や断熱火炎温度の計算は既知であるが, 着火・燃焼遅れといった速度論パラメータもまた組成評価, ないしは将来的なスラスタ設計において重要である. 本研究では反応シミュレーションを用いた速度論的理論計算を実施し, その有用性を評価した.
From previous studies, it has been reported that ionic liquid based on ammonium dinitramide can be liquefied with a total of 4 combinations of two fuels and two melting point depressants. Calculation of specific thrust impulse and adiabatic flame temperature by equilibrium calculation is known, but kinetic parameters such as ignition and combustion delay are also important for composition evaluation or thruster design in the future. In this research, kinetic theoretic calculation using reaction simulation was performed and its usefulness was evaluated.
Description形態: カラー図版あり
Physical characteristics: Original contains color illustrations
KeywordsAmmonium Dinitramide; Ionic liquid; CHEMKIN-PRO; Chemical kinetics; Laminar burning rate; ignition delay
Document TypeTechnical Report
JAXA Category研究開発報告
NASA Subject CategoryPropellants and Fuels
Report NoJAXA-RR-17-008

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