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Several composite propellant compositions containing various concentrations of biuret, a new burning rate suppressant, were formulated and studied to optimize the concentration of biuret in the composite propellant. Biuret was used here for the first time in a composite propellant as a burning rate suppressant. The theoretical properties of the compositions containing different concentrations of biuret were computed by using the NASA CEC-71 programme and the burning rate performances were evaluated. In addition, the sensitivity, thermal and mechanical properties of the compositions were also evaluated. The composition containing ammonium chlorate(VII) (AP) 65%, Al 15%, binder 20% and biuret 0-6% over the batch were prepared. The composition containing 6% biuret over the batch was insensitive to friction and impact. As the amount of biuret was increased, the energy, burning rate and sensitivity decreased, whilst the auto ignition temperature increased. The formulation containing 4% biuret over the batch was found to be the optimum with respect to energy, burning rate, pressure index, and sensitivity.
Słowa kluczowe
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Tom
Strony
3--13
Opis fizyczny
Bibliogr. 12 poz., tab.
Twórcy
autor
- High Energy Materials Research Laboratory, Sutarwadi, Pune-411021, India
autor
- High Energy Materials Research Laboratory, Sutarwadi, Pune-411021, India
autor
- High Energy Materials Research Laboratory, Sutarwadi, Pune-411021, India
autor
- High Energy Materials Research Laboratory, Sutarwadi, Pune-411021, India
Bibliografia
- [1] Curtis D.D., Low Burn Rate Motor Propellant , US Patent 4632715, 1986.
- [2] Nakka R., Richard Nakka’s Experimental Rocketray Web Site, Solid ropellant Burn Rate , http//www.nakka-rocketray.net/burnrate.html, 2003.
- [3] Poulter L.W., Nelson R.W., Smalley R.B. Jr., Hawkins M.C., Robust Propellant Liner and Interfacial Propellant Burning Rate, US Patent 5767221, 1998.
- [4] Chai Y., Tao Z., Jiang Y., Study on the Catalytic Thermal Decomposition of Sodium Azide and Its Correlation with the Burning Rates of Nitrogen Generating Propellants, Tuijin Jishu, 1995, 16, 52-56.
- [5] Williams G.K., Palopoli S.F., Brill T.B., Thermal Decomposition of Energetic Materials 65. Conversion of Insensitive Explosives (NTO, ANTA) and Related Compound to Polymeric Melon-like Cyclic Azine Burn-rate Suppressants, Combust. Flame, 1994 , 98, 197-202.
- [6] Ghorpade V.G., Dey A., Jawale L.S., Kotbagi A.M., Kumar A., Gupta M., Study of Burning Rate Suppressant in AP Based Composite Propellants, Propellants Explos. Pyrotech., 2010, 35, 53-56.
- [7] Gould R.F., Advances in Chemistry Series 88, in: Propellants Manufacture, Hazards, and Testing, American Chemical Society, Washington, DC, 1969.
- [8] Christensen W.N., Development of an Acoustic Emission Strand Burning Technique for Burning Rate Prediction, 14th Joint Propulsion Conference, 1978, 78-984.
- [9] Rinford J.H., Technical Review to Advance Techniques in Acoustical, Electrical and Mechanical Measurements, Bruel and Kjær, DK-2850 NAERUM, Denmark, 1981, 2, 3-32.
- [10] Mallory D.H., Development of Impact Sensitivity Test at Explosive Research Laboratory , Bruceton Pennsylvania, NAVORD, Report No. 4236, 1960.
- [11] Dey A., Ghorpade V.G., Dumbre S.S., Kumar A., Gupta M., Low Burning ate Propellant Composition , Patent application No: 1568/DEL/2008.
- [12] Ghorpade V.G., Dey A., Dumbre S.S., Kumar A., Gupta M., Effect of Different Burning Rate Suppressant in AP Based Composite Propellants, National Seminar on Recent Advances in Energy Systems Combustion Processes , B.I.T, Ranchi, 2007, 43-47.
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-3251f3d5-55c2-4c3b-8c1f-5c67c583913d