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Abstrakty
The measured variations in burning pressure with time for a heterogeneous solid propellant with added ferromagnetic particles of size 0.2-0.5 mm are presented. The laboratory tests were conducted with and without an applied external magnetic field generated by a neodymium magnet. The magnetic induction inside the ballistic chamber in which the experiments were performed, was calculated. Variations in the recorded operating pressure reached up to 60%. At the same time it was noticed that the linear burning rate increased by 7%.
Rocznik
Tom
Strony
791--803
Opis fizyczny
Bibliogr. 18 poz., rys., tab.
Twórcy
autor
- Institute of Industrial Organic Chemistry, Annopol 6, Warsaw, Poland
autor
- Institute of Industrial Organic Chemistry, Annopol 6, Warsaw, Poland
autor
- Institute of Machine Design Fundamentals, Warsaw University of Technology, Poland
Bibliografia
- [1] Borovskoj I.G., Vorozhtsov A.B., Magnetic Field Control of Burning Rate and Thrust in Solid Rocket Motors, J. Propul. Power, 1995, 11(4), 824-829.
- [2] Borovskoy I.G., Vorozhtov A.B., Salko A.E., Magnetogasdynamic Control of Burning Rate of Condensed System, Def. Sci. J., 1995, 45(1), 47-49.
- [3] Spitzer L., Physics of Fully Ionized Gas, Przegląd Techniki Rakietowej, 1961, 40.
- [4] Gaworkow W.A., Electric and Magnetic Field (in Polish), WNT, Warsaw, 1962.
- [5] Lesnikovich A.I., Levchik S.V., Effect of a Magnetic Field on the Burning Rate of Compositions Containing Ferromagnetic Additives, Fiz. Goreniya Vzryva, 1982, 18(3), 68-70.
- [6] Kendrick W.M., Watermeier L.A., Aungst W.P., Pfaff S.P., Effect of a Magnetic Field on Burning Rate of Solid Propellant, Ballistic Research Laboratories, Report No. 1650, June 1973.
- [7] Lenoir J.M, Burning Rate Accelerating Method, Patent US 3617586 A, 1971.
- [8] Zalewski R., Nachman J., Shillor M., Bajkowski J., Dynamic Model for a Magnetorheological Damper, Appl. Math. Model., 2014, 38(9-10), 2366-2376.
- [9] Makowski M., Zalewski R., Vibration Analysis for Vehicle with Vacuum Packed Particles Suspension, J. Theor. Appl. Mech., 2015, 53(1), 109-117.
- [10] Skalski P., Zalewski R., Viscoplastic Properties of an MR Fluid in a Damper, J. Theor. Appl. Mech., 2014, 52(4), 1061-1070.
- [11] PN-V-04014:1997, Homogeneous and Heterogeneous Solid Propellants − Determining the Linear Burning Rate According to the Pressure in Micro-engine (in Polish).
- [12] Bajkowski J., Fluids and MR Dampers, Properties, Design, Research, Modeling and Applications (in Polish), WKŁ, Warsaw, 2014.
- [13] Sutton G.P., Biblarz O., Rocket Propulsion Elements, Wiley, 2010.
- [14] Wolszakiewicz T., Gawor T., Szymczak K., Methodology of Determining the Linear Burning Rate of Solid Propellants (in Polish), Materiały Wysokoenergetyczne, 2009, 1, 107-116.
- [15] Kubota N., Propellants and Explosives. Thermochemical Aspects of Combustion, Wiley-VCH, 2002, pp. 53.
- [16] Fry R.S., Solid Rocket Motor Test and Test Techniques, Component Testing & Verification, Solid Propellant Burning Rate, AIAA Solid Rocket Technical Committee Lecture Series, 36’ Aerospace Sciences Meeting, 1998.
- [17] Shekhar H., Effects of the Burning Rate Index on the Pressure Time Profile of Progressive Burning Tubular Rocket Propellant Configurations, Cent. Eur. J. Energ. Mater., 2015, 12(2), 347-357.
- [18] Shekhar H., Mathematical Formulation and Validation of Muraour’s Linear Burning Rate Law for Solid Rocket Propellants, Cent. Eur. J. Energ. Mater., 2012, 9(4), 353-364
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-9a978832-8eb4-41cb-b7d0-340a4f60e7c2