V. A. Strunin

Bio: V. A. Strunin is an academic researcher. The author has contributed to research in topics: Thermal decomposition & Ammonium perchlorate. The author has an hindex of 1, co-authored 1 publications receiving 3 citations.

Effect of the physical state of the activators on the combustion of composite rocket propellants. I. The applied catalysts

Abstract: The effects on the burning and thermal decomposition of composite rocket propellants, based on ammonium perchlorate and butyl rubber, of oxide coated catalysts applied to tge surface of the ammonium perchlorate crystals and introduced into the propellant in the form of a colloidal suspension are investigated. It is shown that the possibility of changing the burning rate by means of applying the catalyst on the oxidizer crystal surface is determined by the chemical nature, the content of the compounds deposited on the oxidizer surface, and by the structure of the coating formed on the ammonium perchlorate surface. Excluding the agglomeration of the catalytic additives using the developed methods, the variation in their dispersivity and the nature of localization 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.

Catalysis and inhibition of the combustion of ammonium perchlorate based solid propellants

Abstract: Results of studies of the combustion of a composite solid propellant based on ammonium perchlorate are presented. The effect of additives of metal oxides is studied for the high and low-temperature decompositions, linear pyrolysis, and combustion of ammonium perchlorate, the decomposition of HClO4, isobutylene oxidation by oxygen and perchloric acid, and the combustion of propellants with various organic combustibles. It is shown that the efficiency of metal oxides in the reactions of oxidation of isobutylene and propellant combustion is related to the energy of the Me—O bond in the surface oxide layer or the enthalpy of formation of this bond. The extremal nature of the catalytic effect of metal oxides on the burning rate of the propellant is due to the small time of residence of the oxide particles in the zone of intense oxidation-reduction reactions. For this reason, the same additives of metal oxides has different effects on the combustion of the propellant with different organic, combustibles, and the most efficient catalyst can be chosen by a simplified algorithm. The potentials for affecting the composite solid propellant via gas-phase oxidation-reduction reactions is indicated by the effect of additives of organic sources of active species—amines and halides.

Effect of the physical state of activators on the combustion of composite rocket propellants. II. Colloidal inhibitors

Abstract: The effect of inhibitors added as powders and colloidal solutions to propellants on the combustion of ammonium perchlorate composite rocket propellants is investigated. Transformation of chemical governors of the composite-propellant burning rate into the ultradisperse state (<0.05 μm) increases the effectiveness of the inhibitors and decreases their concentration in the propellant provided that particle aggregation is prevented both in synthesis of the governors and during preparation of the propellant. It is shown that multilinear expansion is applicable for a quantitative description of the dependence of the burning rate on the concentration and particle size of the additive.