Anomalous pressure dependence of the burning rate for mixtures of ammonium perchlorate and certain organic fuels

1973 ◽  
Vol 7 (1) ◽  
pp. 48-51
Author(s):  
V. I. Braginskii ◽  
N. N. Bakhman
Keyword(s):  
Burning Rate ◽  
Ammonium Perchlorate ◽  
Pressure Dependence ◽  
Organic Fuels

Pressure dependence of burning rate of ammonium perchlorate-hydrocarbon binder solid propellants

1997 ◽  
Author(s):  
E. Price ◽  
S. Chakravarthy ◽  
R. Sigman ◽  
J. Freeman ◽  
E. Price ◽  
...  
Keyword(s):  
Burning Rate ◽  
Ammonium Perchlorate ◽  
Pressure Dependence ◽  
Solid Propellants

Pressure dependence of burning rate of nitrophenolformaldehyde composite propellants

1980 ◽  
Vol 39 (3) ◽  
pp. 283-286 ◽  
Author(s):  
H.L. Girdhar ◽  
A.J. Arora ◽  
G.N. Malik
Keyword(s):  
Burning Rate ◽  
Pressure Dependence

Effect of Oxidizer-Fuel Mixture Ratio to the Pressure Exponent of Ammonium Perchlorate Based Composite Propellant

2011 ◽  
Vol 110-116 ◽  
pp. 1380-1386
Author(s):  
Amir Aziz ◽  
Wan Khairuddin bin Wan Ali
Keyword(s):  
Experimental Investigation ◽  
Burning Rate ◽  
Ammonium Perchlorate ◽  
Fuel Mixture ◽  
Isophorone Diisocyanate ◽  
Composite Propellant ◽  
Mixture Ratio

In this paper, experimental investigation of pressure exponent in burning rate of composite propellant was conducted. Four sets of different propellant compositions had been prepared with the combination of Ammonium Perchlorate (AP) as an oxidizer, Aluminum (Al) as fuel and Hydroxy-Terminated Polybutadiene (HTPB) as fuel and binder. For each mixture, HTPB binder was fixed at 15% and cured with isophorone diisocyanate (IPDI). By varying AP and Al, the effect of oxidizer-fuel mixture ratio (O/F) on the whole propellant can be determined. The propellant strands were manufactured using compression molded method and burnt in a strand burner using wire technique over a range of pressure from 1atm to 31atm. The results obtained shows that the pressure exponent n, increases with increasing O/F. The highest pressure exponent achieved was 0.561 for propellant p80 which has O/F ratio of 80/20.

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