Model for the Burning Rate and Extinction of Aluminized Polybutadiene Ammonium Perchlorate Composite Propellants

摘要

A combustion model and burning rate equation for an aluminized polybutadiene ammonium perchlorate composite solid propellant was developed in terms of the rate of heat feedback to the propellant surface. The equation was used to calculate the propellant extinction behavior in test chambers with low (or subsonic) exhaust flow, and the C* extinction in test chambers exhausting with supersonic flow (i.e. rocket motors). These calculations agreed well with the observed extinction characteristics of the propellant. (Author)