The diffusion flame structure of an ammonium perchlorate based composite propellant at elevated pressures

2013 ◽  
Vol 34 (1) ◽  
pp. 649-656 ◽  
Author(s):  
T.D. Hedman ◽  
L.J. Groven ◽  
K.Y. Cho ◽  
R.P. Lucht ◽  
S.F. Son
Keyword(s):  
Ammonium Perchlorate ◽  
Diffusion Flame ◽  
Flame Structure ◽  
Composite Propellant ◽  
Elevated Pressures

Experimental observation of the flame structure of a bimodal ammonium perchlorate composite propellant using 5kHz PLIF

2012 ◽  
Vol 159 (1) ◽  
pp. 427-437 ◽  
Author(s):  
T.D. Hedman ◽  
K.Y. Cho ◽  
A. Satija ◽  
L.J. Groven ◽  
R.P. Lucht ◽  
...  
Keyword(s):  
Experimental Observation ◽  
Ammonium Perchlorate ◽  
Flame Structure ◽  
Composite Propellant

POD Scale Analysis of Turbulent Premixed Flame Structure at Elevated Pressures

2019 ◽  
pp. 1-23
Author(s):  
Yaohui Nie ◽  
Jinhua Wang ◽  
Shilong Guo ◽  
Weijie Zhang ◽  
Wu Jin ◽  
...  
Keyword(s):  
Flame Structure ◽  
Premixed Flame ◽  
Scale Analysis ◽  
Turbulent Premixed Flame ◽  
Elevated Pressures ◽  
Turbulent Premixed

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.

The Structure of Laminar Premixed H2-Air Flames at Elevated Pressures

2000 ◽  
Vol 214 (4) ◽  
Author(s):  
M. El-Gamal ◽  
E. Gutheil ◽  
J. Warnatz
Keyword(s):  
Laminar Flame ◽  
Flame Structure ◽  
Ideal Gas ◽  
Fortran Program ◽  
Laminar Flame Speed ◽  
Real Gas ◽  
One Dimensional ◽  
Rocket Propulsion ◽  
Elevated Pressures ◽  
Engine Combustion

In high-pressure flames that occur in many practical combustion devices such as industrial furnaces, rocket propulsion and internal engine combustion, the assumption of an ideal gas is not appropriate. The present paper presents a model that includes modifications of the equation of state, transport and thermodynamic properties. The model is implemented into a Fortran program that was developed to simulate numerically one-dimensional planar premixed flames. The influence of the modifications for the real gas behavior on the laminar flame speed and on flame structure is illustrated for stoichiometric H

Observation on Solid Propellant Ignition Using High Speed Camera: The Effect of Hot Wire Position on the Combustion Flame Contour

2014 ◽  
Vol 71 (2) ◽  
Author(s):  
Wan Khairuddin Wan Ali ◽  
Ang Kiang Long ◽  
Mohammad Nazri Mohd. Jaafar
Keyword(s):  
Solid Propellant ◽  
High Speed ◽  
Flame Structure ◽  
Combustion Process ◽  
Ignition Process ◽  
High Speed Camera ◽  
Hot Wire ◽  
Composite Propellant ◽  
Burning Behavior ◽  
Insight Into

This paper reports on the discovery of unique flame structure of a composite propellant sample under hot wire ignition. The entire combustion process at atmospheric pressure condition was recorded using a high speed camera. Three hot wire orientations were chosen in this experiment for examining their effects on the propellant burning behavior. The results show that the wire orientations are crucial in propellant combustion process, as different flame patterns were observed when the hot wire orientation was altered. This paper provides an important insight into this specific ignition process that can be useful for researchers in the aerospace industry for better design and more realistic simulation results in ignition control.

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