Burning Rate Characteristics of Ammonium Perchloarte-Based Composite Propellant Using Bimodal Ammonium Perchlorate

2008 ◽  
Vol 24 (3) ◽  
pp. 499-506 ◽  
Author(s):  
Makoto Kohga
Keyword(s):  
Burning Rate ◽  
Ammonium Perchlorate ◽  
Composite Propellant

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.

Nano-Ammonium Perchlorate: Preparation, Characterization, and Evaluation in Composite Propellant Formulation

2013 ◽  
Vol 31 (3) ◽  
pp. 192-202 ◽  
Author(s):  
A. Kumari ◽  
Mehilal ◽  
S. Jain ◽  
M. K. Jain ◽  
B. Bhattacharya
Keyword(s):  
Ammonium Perchlorate ◽  
Composite Propellant

Dependence of the burning rate of a composite propellant on the chemical structure of the fuel

1973 ◽  
Vol 6 (4) ◽  
pp. 365-369
Author(s):  
L. D. Romodanova ◽  
V. I. Pepekin ◽  
A. Ya. Apin ◽  
P. F. Pokhil
Keyword(s):  
Burning Rate ◽  
Chemical Structure ◽  
Composite Propellant
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