Abo Bibliothek: Guest
International Journal of Energetic Materials and Chemical Propulsion

Erscheint 6 Ausgaben pro Jahr

ISSN Druckformat: 2150-766X

ISSN Online: 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

Indexed in

PYROLYSIS BEHAVIOR OF A PARAFFIN-BASED THERMOPLASTIC POLYMER USED IN HYBRID ROCKET FUEL

Volumen 18, Ausgabe 4, 2019, pp. 341-354
DOI: 10.1615/IntJEnergeticMaterialsChemProp.2019028195
Get accessGet access

ABSTRAKT

Preliminary experimental studies on the flash pyrolysis behavior of low-melting-temperature thermoplastic (LT) were conducted under typical hybrid rocket operation conditions to obtain the decomposition characteristics of the fuel. LT fuel is a paraffin-added thermoplastic elastomer used in hybrid rocket fuel or solid propellant binders. The temperature profile at or near the surface was measured at 2 MPa chamber pressure and 50 kg m-2 s-1 oxidizer mass flux by a 25 μm thermocouple to estimate the phase structure of the fuel. The paraffin oil was flash pyrolyzed in a pyrolysis temperature range of 758 K to 1,313 K (maximum heating rate: 6,400 K s-1) with a gas chromatography mass spectrometer. Under each temperature condition, the paraffin oil produced a unique pyrolysis mass-spectrometry spectrum. In high-temperature regions, the mass spectra indicate lower molecular weight-range products. Benzene, methylbenzene, and vinylbenzene were obtained as pyrolysis products from the paraffin oil at a pyrolysis temperature of 1,037 K. These results suggest that the formation of aromatic compounds dominated the paraffin-oil pyrolysis process. The pyrolysis behavior of LT fuel was observed by combining the results of the LT-fuel temperature profile and the pyrolysis process in paraffin oil. The result shows that decomposing the LT fuel may form aromatic compounds around the burning surface.

REFERENZEN
  1. Arisawa, H. and Brill, T.B., (1996) Flash Pyrolysis of Hydroxyl-Terminated Polybutadiene (HTPB) I: Analysis and Implications of the Gaseous Products, Combust. Flame, 106(1-2), pp. 131-143.

  2. Chang, P., Wada, Y., Garg, A., Nakayama, H., Kimura, M., and Hori, K., (2015) Combustion and Performance Studies of Glycidyl Azide Polymer and Its Mixtures as Hybrid Rocket Fuel, Int. j. Energetic Mater. Chem. Propuls, 14(3), pp. 221-239.

  3. Chiaverini, M.J., Harting, G.C., Lu, Y.-C., Kuo, K.K., Peretz, A., Jones, H.S., Wygle, B.S., and Arves, J.P., (1999) Pyrolysis Behavior of Hybrid-Rocket Solid Fuels under Rapid Heating Conditions, J. Propuls. Power, 15(6), pp. 888-895.

  4. Gascoin, N., Fau, G., Gillard, P., and Mangeot, A., (2013) Experimental Flash Pyrolysis of High Density Polyethylene under Hybrid Propulsion Conditions, J. Anal. Appl. Pyrol., 101, pp. 45-52.

  5. Hasegawa, H., Isochi, H., Otabe, H., Uematsu, T., Kato, N., Morita, Y., Hori, K., and Akiba, R., (2017) Erosive Burning of Low Melting Point Thermoplastic Solid Propellant, in Proc. of Space Transportation Symp. FY2016, pp. 1-7 (in Japanese).

  6. Isochi, H., Otabe, H., Uematsu, T., Kato, N., Hori, K., Morita, Y., and Akiba, R., (2016) The Low Cost Rocket with Low Melting Temperature Thermoplastic Propellant, in 60th Space Science and Technology Alliance Lecture Meeting (in Japanese).

  7. Kashiwagi, T., (1994) Polymer Combustion and Flammability-Role of the Condensed Phase, in Symp. (Int.) Combust., 25(1), pp. 1423-1437.

  8. Kawabata, Y., Banno, A., Wada, Y., Ozawa, K., Shimada, T., Kato, N., Hori, K., and Nagase, R., (2018) Experimental Investigation of Fuel Regression Rate of Low-Melting-Point Thermoplastic Fuels in the Altering-Intensity Swirling-Oxidizer-Flow-Type Hybrid Rocket Engine, Trans. Japan Soc. Aeronaut. Space Sci. Aerospace Technol. Japan, 16(3), pp. 267-273.

  9. Sinditskii, V. P. , Egorshev, V. Y. , Serushkin, V. V. , and Filatov, S .A . , (2012) Combustion of Energetic Materials Controlled by Condensed-Phase Reactions, Combust. Explos. Shock Waves, 48(1), pp. 81-99.

  10. Takahashi, K., Agglomeration and Ignition of Aluminum Particles in Reaction Zone near Burning Surface of AP Composite Propellants, PhD, Nihon University (in Japanese).

  11. Tsugoshi, T., (2018) Revolution of Evolved Gas Analysis/Mass Spectrometry, Bunseki Kagaku, 67(3), pp. 135-143.

  12. Wada, Y., Jikei, M., Kato, R., Kato, N., and Hori, K., (2012) Application of Low Melting Point Thermo-plastics to Hybrid Rocket Fuel, Trans. Japan Soc. Aeronaut. Space Sci. Aerospace Technol. Japan, 10, pp. 1-5.

  13. Wada, Y., Kato, R., Kato, N., and Hori, K., (2013) Small Rocket Launch Experiment Using Low Melting Point Thermoplastic Fuel/N2O Hybrid Rocket, in Proc. of 49th AIAA/ASME/SAE/AS-EE Joint Propulsion Conf, San Jose, CA, July 14-17, p. 4050.

  14. 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. Japan Soc. Aeronaut. Space Sci. Aerospace Technol. Japan, 12(29), pp. 4-8.

  15. Wada, Y., Kawabata, Y., Kato, R., Kato, N., and Hori, K., (2016) Observation of Combustion Behavior of Low Melting Temperature Fuel for a Hybrid Rocket Using Double Slab Motor, Int. J. Energetic Mater Chem. Propuls., 15(5), pp. 351-369.

Digitales Portal Digitale Bibliothek eBooks Zeitschriften Referenzen und Berichte Forschungssammlungen Preise und Aborichtlinien Begell House Kontakt Language English 中文 Русский Português German French Spain