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REPUBLIC OF SERBIA MINISTRY OF DEFENCE
MINISTRY OF DEFENCE Material Resources Sector Defensive Technologies Department
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An Example of a Successful Erosive Burning REDUCTION in A Small Rocket Motor
MohammEd AMINE BOULAHLIB Military Academy, University of Defence, Belgrade, PhD researcher, mohammed.amine.boulahlib@gmail.com TORCHE RADHIA Military Academy, University of Defence, Belgrade, Master student, torche.ritta@yahoo.com SAŠA ŽIVKOVIĆ Military Technical Institute, Rocket Armament Sector, Belgrade, sasavite@yahoo.com SREDOJE SUBOTIĆ Military Technical Institute, Rocket Armament Sector, Belgrade, sredoje.subotic@gmail.com Nikola GLIGORIJEVIĆ Military Technical Institute, Rocket Armament Sector, Belgrade, nikola.gligorijevic@gmail.com
Abstract: Solid rocket propellant grain is designed for approximately neutral burning, with hollow tube and both burning ends. The outer surface is inhibited. During the initial rocket motor static tests, a kind of irregular propellant burning appeared above 250C, looking like a very strong erosive burning, and its intensity highly increased with temperature. It was concluded that the cause had been the high burning surface to nozzle throat ratio. The intensity of rocket motor combustion irregularity is reduced by suitable grain redesign. The burning surface is increased as well as the nozzle throat area, without significantly affecting the motor performances. In parallel, the surface to nozzle ratio is reduced below the critical threshold appearance of irregular burning. Keywords: Propellant, Double base, Grain, Erosive burning, Port/throat ratio, Thrust, Burning surface.
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