Abstract
AbstractEffects of several liquid burning rate catalysts on rheological properties of composite rocket propellants on the basis of hydroxy‐terminated polybutadiene as a binder and ammonium perchlorate as an oxidizer have been examined. Theoretical explanation of the observed effects of liquid catalysts on certain rheological properties of the mentioned propellants are given. Laboratory procedures for synthesis of used catalysts are described. The results of physico‐chemical characterization of synthesized catalyst are also presented.
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