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
Miscellaneous
No indication
English
Erosive burning<149>of composite solid propellant
AIAA | 1979
|Solid propellant erosive burning
Tema Archive | 1987
|A simplified model for composite propellant burning rate
AIAA | 1999
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