Ujian Pembakaran Propelan Roket Pepejal

2012 ◽  
Author(s):  
Mohammad Nazri Mohd Jaafar ◽  
Wan Khairuddin Wan Ali ◽  
Ahmad Saufi Mohamed Zahri
Keyword(s):  
Key Words ◽  
Burning Rate ◽  
Solid Propellant ◽  
Optimum Composition ◽  
Percentage Composition ◽  
Burning Rates ◽  
Solid Rocket

Komposisi laker dan bahan api yang digunakan dalam fabrikasi propelan pepejal mempengaruhi kadar pembakaran. Kajian ini melihat pengaruh mengubah peratusan komposisi kedua-dua bahan tadi. Hasil ujikaji yang diperolehi, menunjukkan bahawa kadar pembakaran berkurangan dengan pertambahan peratusan laker apabila bahan api dimalarkan pada 29%. Bagaimanapun, apabila laker ditetapkan kepada 22% dan komposisi bahan api diubah-ubah, kadar pembakaran menunjukkan plot parabola dengan komposisi optimum bahan api pada 28.6%. Kata kunci: Kalium nitrat; sulfur; aluminium; kadar pembakaran; roket pepejal The composition of lacquer and fuel used during fabrication of solid propellant affects the burning rates. This study shows the effect of varying the percentage composition of both items. Results obtained show that the burning rates reduce with increase in laker percentage when fuel was set constant at 29%. However; when lacquer was set constant at 22% and at varied fuel compositions, the burning rates show a parabolic plot with the optimum composition at 28.6% fuel. Key words: Kalium nitrate; sulfur; aluminium; burning rate; solid rocket

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 Burning Rate Enhancement Analysis of End-Burning Solid Propellant Grains Based on X-Ray Real-Time Radiography

2020 ◽  
Vol 2020 ◽  
pp. 1-9
Author(s):  
Wei Xianggeng ◽  
Bo Tao ◽  
Wang Pengbo ◽  
Ma Xinjian ◽  
Lou Yongchun ◽  
...  
Keyword(s):  
Burning Rate ◽  
Real Time ◽  
Solid Propellant ◽  
Burning Surface ◽  
Rocket Motor ◽  
Operating Pressure ◽  
Solid Rocket Motor ◽  
X Ray ◽  
The Real ◽  
Solid Rocket

Unexpected pressure rise may occur in the end-burning grain solid rocket motor. It is generally believed that this phenomenon is caused by the nonparallel layer combustion of the burning surface, resulting in the increase of burning rate along the inhibitor. In order to explain the cause of this phenomenon, the experimental investigation on four different end configurations were carried out. Based on the X-ray real-time radiography (RTR) technique, a new method for determining the dynamic burning rate of propellant and obtaining the real-time end-burning profile was developed. From the real-time images of the burning surface, it is found that there was a phenomenon of nonuniform burning surface displacement in the end-burning grain solid rocket motor. Through image processing, the real-time burning rate of grain center line and the real-time cone angle are obtained. Based on the analysis of the real-time burning rate at different positions of the end surface, the end face cone burning process in the motor working process is obtained. The closer to the shell, the higher the burning rate of the propellant. Considering the actual structure of this end-burning grain motor, it is speculated that the main cause of the cone burning of the grain may be due to the heat conduction of the metal wall. By adjusting the initial shape of the grain end surface, the operating pressure of the combustion chamber can be basically unchanged, so as to meet the mission requirements. The results show that the method can measure the burning rate of solid propellant in real time and provide support for the study of nonuniform combustion of solid propellant.

NON-STATIONARY BEHAVIOR OF A SOLID PROPELLANT CHARGE FOR NOZZLELESS SOLID ROCKET MOTORS UNDER GAS-DYNAMIC LOAD

2021 ◽  
pp. 48-59
Author(s):  
I.G. Voropaeva ◽  
◽  
A.A. Kozulin ◽  
L.L. Min’kov ◽  
E.R. Shrager ◽  
...  
Keyword(s):  
Burning Rate ◽  
Solid Propellant ◽  
Solid Mechanics ◽  
Stokes Equations ◽  
Combustion Products ◽  
Conjugate Problem ◽  
Navier Stokes ◽  
Solid Rocket Motor ◽  
Propellant Charge ◽  
Solid Rocket

The numerical solution to a conjugate problem of an unsteady flow of combustion products in a flow path of the nozzleless solid rocket motor (SRM) and the oscillation of a solid propellant charge under the action of the forces directed from combustion products is considered. The Navier-Stokes equations for a compressible viscous gas are used to mathematically describe the flow of the combustion products. To model the charge oscillations, the equations of solid mechanics are applied, which take into account the propellant hyperelasticity. Pressure distributions and the propellant burning rate along the charge channel are presented for different models of the propellant burning rate. It is revealed that at the stage of SRM design, the use of the burning rate law, determined by pressure in the head of the combustion chamber, is more preferable in order to assess the internal ballistic characteristics. The solution to the conjugate problem shows that in the nozzleless SRM with the propellant having low Young's modulus, resonance can occur, which causes uncontrolled charge oscillations.

scholarly journals Effects of Nano-Sized Al on the Combustion Performance of Fuel Rich Solid Rocket Propellants

2016 ◽  
Vol 18 (3) ◽  
pp. 197 ◽  
Author(s):  
W.Q. Pang ◽  
F.Q. Zhao ◽  
L.T. DeLuca ◽  
C. Kappenstein ◽  
H.X. Xu ◽  
...  
Keyword(s):  
Burning Rate ◽  
Mass Fraction ◽  
Impact Sensitivity ◽  
Heat Of Combustion ◽  
Nominal Composition ◽  
Rocket Propellants ◽  
Burning Rates ◽  
Solid Rocket ◽  
Friction Sensitivity ◽  
Solid Rocket Propellants

Several industrial- and research – type fuel rich solid rocket propellants containing nano-metric aluminum metal particles, featuring the same nominal composition, were prepared and experimentally analyzed. The effects of nano-sized aluminum (nAl) on the rheological properties of metal/HTPB slurries and fuel rich solid propellant slurries were investigated. The energetic properties (heat of combustion and density) and the hazardous properties (impact sensitivity and friction sensitivity) of propellants prepared were analyzed and the properties mentioned above compared to those of a conventional aluminized (micro-Al, mAl) propellant. The strand burning rate and the associated combustion fl ame structure of propellants were also determined. The results show that nAl powder is nearly “round” or “ellipse” shaped, which is different from the tested micrometric Al used as a reference metal fuel. Two kinds of Al (nAl and mAl) powder can be dispersed in HTPB binder suffi ciently. The density of propellant decreases with increasing mass fraction of nAl powder; the measured heat of combustion, friction sensitivity, and impact sensitivity of propellants increase with increasing mass fraction of nAl powder in the formulation. The burning rates of fuel rich propellant increase with increasing pressure, and the burning rate of the propellant loaded with 20% mass fraction of nAl powder increases 77.2% at 1 MPa, the pressure exponent of propellant increase a little with increasing mass fraction of nAl powder in the explored pressure ranges.

Burning Rate of Solid Propellant Ingredients, Part 1: Pressure and Initial Temperature Effects

1999 ◽  
Vol 15 (6) ◽  
pp. 740-747 ◽  
Author(s):  
A. I. Atwood ◽  
T. L. Boggs ◽  
P. O. Curran ◽  
T. P. Parr ◽  
D. M. Hanson-Parr ◽  
...  
Keyword(s):  
Burning Rate ◽  
Temperature Effects ◽  
Solid Propellant ◽  
Initial Temperature
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