Reported study of composite-propellant burning summarizes recent advances in understanding behavior of propellant formulations based on ammonium perchlorate (AOP), binder, and aluminum in various proportions and particle size distributions. Approach presented incorporates adapted version of earlier model for monopropellant AP. Objective is to predict burning-rate characteristics of composite propellants at high pressure.
Equations for Composite-Propellant Burning
NASA Tech Briefs ; 7 , 1
1983-03-01
Sonstige
Keine Angabe
Englisch
Erosive burning<149>of composite solid propellant
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