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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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IMPROVEMENT OF COMBUSTION EFFICIENCY USING A BAFFLE PLATE FOR A LT/GOX HYBRID ROCKET MOTOR

Volume 18, Numéro 4, 2019, pp. 367-383
DOI: 10.1615/IntJEnergeticMaterialsChemProp.2019028124
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RÉSUMÉ

In this study, we developed a high-performance, high-thrust hybrid rocket motor using low-melting-point thermoplastic (LT) fuel and a baffle plate compared to conventional hybrid rocket motors using a low regression rate fuel such as hydroxyl terminal polybutadiene (HTPB). LT fuel has excellent mechanical and adhesive properties, as well as a high regression rate compared to conventional hybrid rocket fuel. Static firing tests lasting 10 s using the LT fuel and gaseous oxygen (GOX) were conducted to investigate the influence of different geometric-shaped baffle plates on the characteristic velocity. Tests with baffle plates with two or more holes improved the characteristic velocities and bottom chamber pressures compared to tests without the baffle plate. In the test using a baffle plate with two rows of holes, no improvement in the characteristic velocity was confirmed. This was because the oxidizer and fuel passed through different holes and did not mix. The characteristic velocity using a baffle plate having three holes was ~ 10% higher than without the baffle plate, because the fuel and the oxidizer passed through a common hole and the combustion gas stayed at the top of the baffle plate. In all the experiments, the fuel regression rate was higher than the conventional value, as the back end of the fuel was regressed by the baffle plate and unburned fuel was discharged. These results suggested that when two more baffle plates are set, or an after-combustion chamber is provided on the downstream side, the characteristic velocity is improved.

RÉFÉRENCES
  1. Bettella, A., Lazzarin, M., Bellomo, N., Barato, F., and Pavarin, D., (2011) Testing and CFD Simulation of Diaphragm Hybrid Rocket Motors, 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conf. Exhibit, AIAA Paper No. 2011-6023.

  2. Ishiguro, T., Shinohara, K., Sakio, K., and Nakagawa, I., (2011) A Study on Combustion Efficiency of Paraffin-Based Hybrid Rockets, 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conf. Exhibit, AIAA Paper No. 2011-5679.

  3. Karabeyoglu, M.A., Cantwell, B.J., and Altman, D., (2001) Development and Testing of Parafin-Based Hybrid Rocket Fuels, 37th Joint Propulsion Conf. Exhibit, AIAA Paper No. 2001-4503.

  4. Kawabata, Y., Wada, Y., Kato, N., Hori, K., and Nagase, R., (2016) Study on Improvement of Mechanical Characteristics of LT Fuels for Hybrid Rocket, 13th Int. Conf. on Flow Dynamics, Paper No. OS8-22.

  5. Lazzarin, M., Bellomo, N., Barato, F., and Grosse, M., (2010) Numerical Investigation of the Effect of a Diaphragm on the Performance of a Hybrid Rocket Motor, 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conf. Exhibit, AIAA Paper No. 2010-7033.

  6. Sutton, P.G. and Biblarz, O., (2001) Rocket Propulsion Elements, 7th ed., Hoboken, NJ: Wiley.

  7. Wada, Y., Jikei, M., Kato, R., Kato, N., and Hori, K., (2012) Application of Low Melting Point Thermoplastics to Hybrid Rocket Fuel, Trans. Jpn. Soc. Aeronaut. Space Sci., 10(28), pp. 1-5.

  8. Wada, Y., Kato, R., Kato, N., and Hori, K., (2013) Small Rocket Launch Experiment Using Low Melting Point Temperature Thermoplastic Fuel/N2O Hybrid Rocket, 49th AIAA/ASME/SAE/ASEE Joint Propulsion. Conf., AIAA Paper No. 2013-5050.

  9. Wada, Y., Kawabata, Y., Shinnakazaki, K., Kato, R., Kato, N., and Hori, K., (2014) A Study on Combustion Efficiency Improvement of Low Melting Temperature Thermoplastics as a Hybrid Rocket Fuel, Trans. JSASS Aerospace Tech. Jpn., 12(29), pp. 9-14.

  10. Yuasa, S., Yamamoto, K., Hachiya, H., and Kitagawa, K., (2001) Development of a Small Sounding Hybrid Rocket with a Swirling-Oxidizer-Type Engine, 37th Joint Propulsion Conf. Exhibit, AIAA Paper 2001-3537.

CITÉ PAR
  1. Kawabata Yo, Kimura Masaya, Wada Yutaka, Nagase Ryo, Kato Ryuichi, Kato Nobuji, Hori Keiichi, Matsui Takafumi, Experimental Study on 5 kN Thrust Level Hybrid Rocket Motor Using the Low-Melting-Point Thermoplastic Fuel, AIAA Propulsion and Energy 2020 Forum, 2020. Crossref

  2. Hill Colin, Evaluation of a Paraffin/Nitrous Oxide Hybrid Rocket Motor with Passive Mixing Device, AIAA SCITECH 2022 Forum, 2022. Crossref

  3. Hill Colin D., Nelson Will, Johansen Craig T., Evaluation of a Paraffin/Nitrous Oxide Hybrid Rocket Motor with a Passive Mixing Device, Journal of Propulsion and Power, 2022. Crossref

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