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Development of a Composite Propellant Formulation with a High Performance Index Using a Pressure Casting Technique

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Języki publikacji
EN
Abstrakty
EN
There is a continuous demand for high performance composite propellant formulations to meet future requirements. The performance of composite propellant formulations can be enhanced by the addition of energetic oxidizers, like ADN/HNF as well as an energetic binder & a plasticizer. However, on incorporation of energetic ingredients, the composition becomes sensitive, and thus processing, handling and transportation pose a greater threat. Therefore, a moderately high burn rate composition having a burn rate ~ 13-14 mmźs -1 at 7000 kPa was tailored by increasing the solid loading of the propellant from 85.15% to 87.27% with the help of ammonium perchlorate and process aids without affecting the burn rate and mechanical properties. The tailored composition was studied for different properties such as end of mix viscosity, density, mechanical & ballistic properties. The evaluated data reveal that the end of mix viscosity of the tailored composition is higher than the base composition, i.e., 672 Paźs and 2340 Paźs at the same temperature; however, this viscosity was castable using a pressure casting technique. The properties of the cured propellant reveal that there is an enhancement of density from 1.74 gźcm -3 to 1.79 gźcm -3 with no other changes in mechanical properties. The performance index of the tailored composition has been increased from 416 to 437, well supported by results of ballistic evaluation motors of 2 kg.
Rocznik
Strony
49--58
Opis fizyczny
Bibliogr. 9 poz.
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autor
autor
Bibliografia
  • [1] Propellants, Manufacturing, Hazards and Testing, American Chemical Society, (Boyars C., Klager K., Eds), Washington D.C, 1969, p. 88.
  • [2] Langlet A. , Wingborg N., Ostmark H., ADN: A New High Performance Oxidizer for Solid Propellants, International Journal of Energetic Materials and Chemical Propulsion, 1997, 4, 1-6.
  • [3] Gadiot G.M.H.J.L., Mul J.M., Meulenbrugge J.J., Korting P.A.O.G., Schnorkh A.J., Schoyer H.F.R., New Solid Propellants Based on Energetic Binders and HNF, Acta Astronautica, 1993, 29, 771-779.
  • [4] Gadiot G.M.H.J.L, Hoffmans D.W., Korting P.A.O.G., Leenders A.P.M., Clean Propellants for Commercial Applications, International Journal of Energetic Materials and Chemical Propulsion, 1997, 4, 1-6.
  • [5] Schoyer H.F.R., Schnorkh A.J., Korting P.A.O.G., van Lit P.J., First Experimental Results of an HNF/Al/GAP Solid Propellant, AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, T.L. 33rd, Seattle, WA, July 6-9, 1997.
  • [6] Muthiah R.M., Varghese, Rao S.S., Ninan K.N., Krishnamurthy V.N. Realization of an Eco-friendly Solid Propellant Based on HTPB-HMX-AP System for Launch Vehicle Applications, International Journal of Energetic Materials and Chemical Propulsion, 1997, 4, 1-6.
  • [7] Yang R., An H., Tan H., Combustion and Thermal Decomposition of HNIW and HTPB/HNIW Propellants with Additives, Combustion and Flame, 2003, 135, 463-473.
  • [8] Couturier R., Advanced Energetic Binder Propellants, in: Solid Rocket Propulsion Technology, (A. Davenas, Ed.), Pergamon Press, Oxford, 1993, pp. 510-511.
  • [9] Caveny L.H., Pokrocos L. M., Lelshain G.R., High Pressure Burning Rates of Multibase Propellants, Department of Aerospace and Mechanical Sciences, Princeton University, New Jersey, AMS-1377, 1977, 75.
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-article-BAT1-0041-0076
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