Combustion kinetics simulation studies for solid composite propellant containing nano-iron oxide burning rate catalyst

2018 ◽  
Author(s):  
Luiz E. Almeida ◽  
Rene F. Gonçalves ◽  
Koshun Iha ◽  
Jose A. Rocco
Keyword(s):  
Iron Oxide ◽  
Burning Rate ◽  
Simulation Studies ◽  
Combustion Kinetics ◽  
Composite Propellant ◽  
Kinetics Simulation ◽  
Solid 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.

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

Effect of aluminum and iron oxide on the temperature coefficient of the burning rate of condensed mixtures

1973 ◽  
Vol 6 (4) ◽  
pp. 374-376 ◽  
Author(s):  
V. V. Zhalnin ◽  
N. N. Bakhman ◽  
G. V. Lukashenya ◽  
Yu. S. Kichin
Keyword(s):  
Iron Oxide ◽  
Temperature Coefficient ◽  
Burning Rate

scholarly journals Propelan Pepejal Kalium Nitrat Difabrikasi Kaedah Pengacuanan Mampat

2012 ◽  
Author(s):  
Mohammad Nazri Mohd. Ja’afar ◽  
Wan Khairuddin Wan Ali ◽  
Md Nizam Dahalan ◽  
Rizalman Mamat
Keyword(s):  
Burning Rate ◽  
Atmospheric Pressure ◽  
Solid Propellant ◽  
Strong Relationship ◽  
Potassium Nitrate ◽  
Experimental Results ◽  
Test Rig ◽  
Composite Propellant ◽  
Burning Rates ◽  
Different Characteristics

Propelan pepejal untuk kegunaan roket berbahan dorong pepejal yang telah dihasilkan di Universiti Teknologi Malaysia (UTM) adalah dari kumpulan propelan komposit kalium nitrat sebagai pengoksida dan sukros sebagai bahan api. Antara kaedah fabrikasi propelan adalah teknik pembentukan (forming), penyemperitan (extrusion), tuangan (casting) dan pengacuanan mampat (compressed moulding). Semua kaedah ini telah menghasilkan pelbagai propelan dengan sifat serta gaya laku yang berbeza–beza. Bergantung kepada bagaimana ia difabrikasi, propelan ini telah menunjukkan perkaitan sifat mekanikal yang begitu ketara. Dari setiap kaedah, propelan dibentuk mengikut satu bentuk serta dimensi yang piawai. Ujian kadar pembakaran dibuat ke atas setiap jalur propelan menggunakan alat uji kaji (test rig) yang telah direka bentuk. Ujian kadar pembakaran dilakukan pada tekanan atmosfera. Melalui ujian ini, kadar pembakaran propelan telah diperolehi. Hasil uji kaji menunjukkan kadar pembakaran propelan yang menggunakan teknik pembentukan dan teknik pengacuanan mampat masing–masing adalah 1.033 cm/s dan 0.429 cm/s. Manakala kaedah penyemperitan dan kaedah tuangan didapati tidak sesuai kerana sifat propelan kalium nitrat–sukros yang likat. Hasil uji kaji menunjukkan kaedah pengacuanan mampat ialah kaedah yang paling sesuai berbanding kaedah yang lain kerana dapat menghasilkan propelan yang seragam dan stabil. Kata kunci: Propelan; komposit; pengoksida; bahan api; kadar pembakaran Solid propellant used on solid fuel rocket developed at Universiti Teknologi Malaysia (UTM) is from the composite propellant group with potassium nitrate as the oxidizer and sucrose as the fuel. Among the propellant fabrication techniques are forming, extrusion, casting and compressed moulding. All of these techniques are used to fabricate several types of propellant with different characteristics and performances. Depending upon the technique of fabrication, these propellants have shown strong relationship with their mechanical properties. With every technique, the propellants are formed according to a standard shape and dimension. Burning rate tests were performed for each propellant strand fabricated using the test rig designed. The burning rate tests were performed at atmospheric pressure. Through this test, the propellant burning rates were obtained. Experimental results show that the burning rate for propellant developed using forming and compressed moulding are 1.033 cm/s and 0.429 cm/s, respectively. Meanwhile, the extrusion and casting methods were found not suitable due to the property of potassium nitrate–sucrose that is viscous. Experimental results show that the pressed moulding method is the most suitable method compared to the other techniques since it can produce propellant that is uniform and stable. Key words: Propellant; composite; oxidizer; fuel; burning rates

scholarly journals Research of High-Temperature Heat and Mass Transfer and Kinetics of Phase Transformations during combustion higher alkanes in the air

2015 ◽  
Vol 16 (2) ◽  
pp. 347-350
Author(s):  
S.G. Orlovska ◽  
A.O. Odnostalko ◽  
F.F. Karimova ◽  
M.S. Shkoropado
Keyword(s):  
Mass Transfer ◽  
High Temperature ◽  
Phase Transformations ◽  
Burning Rate ◽  
Heat And Mass Transfer ◽  
Rate Constants ◽  
Room Temperature ◽  
Combustion Kinetics ◽  
Temperature Heat ◽  
Kinetics Of

 The paper presents a study of high-temperature heat and mass transfer and combustion kinetics of octadecane particle in room temperature air taking in consideration fuel heating, melting and evaporation. The consecutive stages of droplet combustion are described. Burning rate constants and flame heights are determined for droplets with different initial diameters

Recent progress in evaluating the detonation characteristics of solid-composite propellant.

AIAA Journal ◽  
1968 ◽  
Vol 6 (3) ◽  
pp. 489-496
Author(s):  
R. B. ELWELL ◽  
O. R. IRWIN ◽  
P. K. SALZMAN ◽  
N. H. VALOR
Keyword(s):  
Recent Progress ◽  
Composite Propellant ◽  
Solid Composite Propellant ◽  
Detonation Characteristics
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