EFFECT OF THE PHYSICAL STATE OF THE ACTIVATORS ON THE COMBUSTION OF COMPOSITE ROCKET PROPELLANTS .1. THE APPLIED CATALYSTS

The effects on the burning and thermal decomposition of composite rock et propellants, based on ammonium perchlorate and butyl rubber, of oxi de coated catalysts applied to the surface of the ammonium perchlorate crystals and introduced into the propellant in the form of a colloida l suspension are investigated. It is shown that the possibility of cha nging the burning rate by means of applying the catalyst on the oxidiz er crystal surface is determined by the chemical nature, the content o f the compounds deposited on the oxidizer surface, and by the structur e of the coating formed on the ammonium perchlorate surface. Excluding the agglomeration of the catalytic additives using the developed meth ods, the variation in their dispersivity and the nature of localizatio n in the propellant are the indicators of the propellant's performance efficiency within the region of small additive concentrations (up to 0.5%) in the propellant.