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8221829 
Journal Article 
Combustion mechanism of high energy composite propellants (V) - combustion of azide/nitramine propellants 
Bazaki, H; Iida, A; Mitarai, Y 
1998 
Japan Explosives Society 
Tokyo, Japan 
59 
1 
30-35 
English 
The combustion wave structure was examined by using fine thermocouples in order to elucidate the control process of burning rate of azide/nitramine propellants. From the experiments, it was found that the burning rate of AMMO(3-azidemethyl-3′-methyloxetane)/EDNA(ethylenedinitramine) propellant was higher than that of AMMO/HMX(cyclotetramethylenetetranitramine) propellant and the pressure exponent of AMMO/EDNA propellant was lower than that of AMMO/HMX propellant. The temperature profile in the combustion waves of the propellants revealed that there was a large heat release at the burning surface. This exothermic decomposition reaction at the burning surface is found to be mainly responsible for the burning rate of AMMO/EDNA and AMMO/HMX propellants. It is explained by the larger heat release of AMMO/EDNA propellant at the burning surface that AMMO/EDNA propellant has the higher burning rate than AMMO/HMX propellant.