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A review, with 29 refs., of literature data and author's own papers on rheolog., ballistic and technol. properties of solid rocket propeiiarńs based on NH4ClO4- a,ω-Dihydroxypolybutadiene, a,ω-dicarboxypolybutadiene, dioctyl adipate, isocyanates, ferrocenes, Fe2O3 butacene, catocene and Ai powder were used as additives. Source

A mixt. of hydroxyl-terminated poly butadiene, dioctyl adipate plasticizer, dimeryl diisocyanate curing agent, NH4CIO4, AI powder and 2, 2′-bis(ethylferrocenyl)propane, lecithin additive, glycerol soln, of oxalic acid, 1, 1′-isophthaloyl bis(2-methylaziridine) and (2, 2′-methylene-bis(6-tert-butyl-4-methylphenol) antioxidant was prepd. as heterogeneous propellant slurry and studied for viscosity as function of time and temp. The results were presented as logarithmic equations. The propellant slurry had a relatively long pot life time. Source

Florczak B.,Instytut Przemyslu Organicznego | Stokowski P.,Military University of Technology | Maranda A.,Military University of Technology
Przemysl Chemiczny

Twenty-two hydroxyl-terminated polybutadiene-based binders for propellants were prepd. by addn. of dioctyladipate plasticizer, Fe2O3 nanoparticles, 2,2'-bis(ethylferrocenyl)propane (I) or Cu2Cr 2O5 additives and dilsocyanate curing agents to 3 rubbers and then studied for viscosity changes during storage at 65°C for 180 min. An increase in the binder viscosity was obsd. esp. when the binders contained I additive. The binders based on com. liq. rubbers were more stable than that based on a rubber produced under lab. conditions. Source

Florczak B.,Instytut Przemyslu Organicznego
Przemysl Chemiczny

A review, with 47 refs., of oxidizers, nitrocompds. and binders used in composite solid propellants. For some 3-component propellants, the thermodynamic parameters were calcd. by using a computer program. Source

Five com. solid rocket propeiant were tested for tensiie strength to det. the force-elongation and stress-strain curves. The tensiie strength was 1.0-6.5 MPa and the elongation at rupture 0.062-0.94. No correlation between the tensile strength and combustion rate of the propelants was obsd. Source

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