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Measurement of Energy Emitted by Pyrogenic Tablets Used for Ignition of Solid Rocket Propellants

Treść / Zawartość
Identyfikatory
Warianty tytułu
Języki publikacji
EN
Abstrakty
EN
In order to ignite a solid rocket propellant special igniting devices – pyrogenic tablets – must be used. The reported research was aimed at finding the best material for such pyrogenic tablets, which would successfully replace the still frequently used black powder. The measurement of heat, absorbed by the rocket propellant from various kinds of pyrogenic tablets against time, as well as tests of the ignition of the rocket propellant in a stationary engine, were performed. It was concluded, that of all of the mixtures considered, the best material for pyrogenic tablets was a mixture of 25% Zr and 75% KNO3.
Rocznik
Strony
359--375
Opis fizyczny
Bibliogr. 17 poz., rys., tab.
Twórcy
  • Institute of Industrial Organic Chemistry, Annopol 6, 03-236 Warsaw, Poland
  • Institute of Fundamental Technological Research, Pawinskiego 5b, 02-106 Warsaw, Poland
Bibliografia
  • [1] Gransden J.I., Taylor M.J., Study of Confined Pyrotechnic Compositions for Medium/Large Calibre Gun Igniter Applications, Propellants Explos. Pyrotech., 2007, 32, 6-11.
  • [2] Bhingarkar V., Singh H., Influence of Cellulosic Binders on Sensitivity and Combustion, Def. Sci. J., 2006, 56(3), 345-351.
  • [3] Wildegger-Gaissmaier E., Johnston I.R., Ignition of a Granular Propellant Bed, Combust. Flame, 1996, 106, 219-230.
  • [4] Kuwahara T., Tohara C., Ignition Characteristics of Zr/BaCrO4 Pyrolant, Propellants Explos. Pyrotech., 2002, 27, 284-289.
  • [5] Kuwahara T., Tohara C., Wang C.H., Static Electric Sensitivity Characteristics of Zr/BaCrO4 Pyrolants, Propellants Explos. Pyrotech., 2004, 29, 56-61.
  • [6] Lee J.S., Hsu C.K., The Effect of Different Zirconium on Thermal Behaviors for Zr/KClO4 Priming Compositions, Thermochim. Acta, 2001, 367-368.
  • [7] Lee J.S., Thermal Properties and Firing Characteristics of the Zr/KClO4/Viton A Priming Compositions, Thermochim. Acta, 2002, 392-393,147-152.
  • [8] Torecki S., Rocket Engines (in Polish: Silniki rakietowe), Warszawa, 1984.
  • [9] Backstead M.W., Puduppakkam K., Thakre P., Yang V., Modeling of Combustion and Ignition of Solid – Propellant Ingredients, Prog. Energy Combust. Sci., 2007, 33, 497-551.
  • [10] Zalewski R., Wolszakiewicz T., Experimental Studies on Fundamental Mechanical Properties of Homogeneous Solid Rocket Propellants, Przem. Chem., 2012, 91(9), 1825-1829.
  • [11] Zalewski R., Wolszakiewicz T., Bajkowski J., Effect of Temperature on Fundamental Mechanical Properties of Homogeneous Solid Propellants, Przem. Chem., 2012, 91(9), 1830-1833.
  • [12] Wolszakiewicz T., Gawor T., Zalewski R., Ballistic Analysis of Homogeneous Solid Propellants Subjected to Thermal and Mechanical Pre-loading Preliminary Communication, Przem. Chem., 2012, 91(9), 1854-1857.
  • [13] Hall J.G., Hertzberg A., Recent Advances in Transient Surface Thermometry, Jet Propul., 1958, 28(11), 719-723.
  • [14] Bird G.A., Molecular Gas Dynamics and the Direct Simulation of Gas Flows, Clarendon Press, Oxford, 1994.
  • [15] Hartunian R.A., Varwig R.L. On Thin Film Heat Transfer Measurements in Shock Tubes and Shock Tunnels, Phys. Fluids, 1962, 5(2), 169-174.
  • [16] Carslaw H.S., Jaeger J.C., Conduction of Heat in Solids, Oxford University Press, 1959.
  • [17] Walenta Z.A., Analogue Networks for High Heat-transfer Rate Measurements, UTIAS Technical Note, November 1964, No. 84, (AFOSR 65-0261).
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-fe455f91-d898-4926-8b29-b9e795e9303d
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