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International Journal of Energetic Materials and Chemical Propulsion

Publication de 6  numéros par an

ISSN Imprimer: 2150-766X

ISSN En ligne: 2150-7678

The Impact Factor measures the average number of citations received in a particular year by papers published in the journal during the two preceding years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) IF: 0.7 To calculate the five year Impact Factor, citations are counted in 2017 to the previous five years and divided by the source items published in the previous five years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) 5-Year IF: 0.7 The Immediacy Index is the average number of times an article is cited in the year it is published. The journal Immediacy Index indicates how quickly articles in a journal are cited. Immediacy Index: 0.1 The Eigenfactor score, developed by Jevin West and Carl Bergstrom at the University of Washington, is a rating of the total importance of a scientific journal. Journals are rated according to the number of incoming citations, with citations from highly ranked journals weighted to make a larger contribution to the eigenfactor than those from poorly ranked journals. Eigenfactor: 0.00016 The Journal Citation Indicator (JCI) is a single measurement of the field-normalized citation impact of journals in the Web of Science Core Collection across disciplines. The key words here are that the metric is normalized and cross-disciplinary. JCI: 0.18 SJR: 0.313 SNIP: 0.6 CiteScore™:: 1.6 H-Index: 16

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COMBUSTION CHARACTERISTICS OF HAN-BASED LIQUID MONOPROPELLANT

Volume 7, Numéro 2, 2008, pp. 123-137
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v7.i2.30
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RÉSUMÉ

A new composition of the hydroxyl ammonium nitrate (HAN)-based solution containing ammonium nitrate, methanol, and water had been developed for monopropellant in a reaction control system (RCS) as an alternative to conventional hydrazine. Comparing this solution with hydrazine, Isp is 20% higher, density is 1.4 times, the freezing point is much lower, and the toxicity is low, which makes this solution promising as a RCS propellant. The linear burning rate of the solution is moderate at the operating pressures of an RCS thruster. However, it was found that the linear burning rate had some characteristics whose mechanisms had not been understood. The combustion mechanism of this solution was investigated, the burning behavior was observed using a medium speed camera, and a temperature profile for the combustion wave was measured with a fine 2.5 μm-diameter thermocouple. From these results, the instability of the liquid interface may trigger a sudden increase in the burning rate to a violently high region, and methanol was found to be effective in reducing the bubble growth rate in the solution. For RCS thruster use, reactivity with several catalysts was evaluated in an open-cup test. Consequently, the S405 catalyst for hydrazine showed the best performance among Pt-based, Pd-based, Ru-based, Ir-based, and S405 catalysts. Thruster tests were conducted successfully using S405 in both the pulsing and continuous modes. As a result, it was found that S405 has little effect in activation of the reaction of methanol contained in the propellant. High-concentration Pd catalyst was found to improve the decomposition characteristic of the solution.

RÉFÉRENCES
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CITÉ PAR
  1. Katsumi T., Inoue T., Nakatsuka J., Hasegawa K., Kobayashi K., Sawai Sh., Hori K., HAN-based green propellant, application, and its combustion mechanism, Combustion, Explosion, and Shock Waves, 48, 5, 2012. Crossref

  2. Kakami Akira, Ideta Keisuke, Ishibashi Takuya, Tachibana Takeshi, One Newton thruster by plasma-assisted combustion of HAN-based monopropellant, 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2012. Crossref

  3. Kakami Akira, Ishibashi Takuya, Ideta Keisuke, Tachibana Takeshi, One-Newton class thruster using arc discharge assisted combustion of nitrous oxide/ethanol bipropellant, Vacuum, 110, 2014. Crossref

  4. Atamanov M., Amrousse R., Jandosov J., Hori K., Kerimkulova A., Chenchik D., Kolesnikov B., Combustion Characteristics of HAN-based Green Propellant Assisted with Nanoporous Active Carbons, Eurasian Chemico-Technological Journal, 19, 3, 2017. Crossref

  5. Kakami Akira, Kuranaga Atsushi, Yano Yasuyuki, Premixing-type liquefied gas bipropellant thruster using nitrous oxide/dimethyl ether, Aerospace Science and Technology, 94, 2019. Crossref

  6. Esparza Alan A., Shafirovich Evgeny, Thermoanalytical Study of Hydroxylammonium Nitrate Decomposition at High Pressures, AIAA Propulsion and Energy 2019 Forum, 2019. Crossref

  7. Nosseir Ahmed E. S., Cervone Angelo, Pasini Angelo, Review of State-of-the-Art Green Monopropellants: For Propulsion Systems Analysts and Designers, Aerospace, 8, 1, 2021. Crossref

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