Withdrawal: Manufacture of solid propellant using epoxy resin and potassium nitrate

2020 ◽  
Author(s):  
Jose A. Rocco ◽  
Marcela G. Domingues ◽  
Rene F. Gonçalves ◽  
Ellen C. Rosa ◽  
Daniel Bontorin ◽  
...  
Keyword(s):  
Epoxy Resin ◽  
Solid Propellant ◽  
Potassium Nitrate

Manufacture of solid propellant using epoxy resin and potassium nitrate

2020 ◽  
Author(s):  
Jose A. Rocco ◽  
Marcela G. Domingues ◽  
Rene F. Gonçalves ◽  
Ellen C. Rosa ◽  
Daniel Bontorin ◽  
...  
Keyword(s):  
Epoxy Resin ◽  
Solid Propellant ◽  
Potassium Nitrate

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

Copper (II) Phthalocyanine Effects On Solid Propellant Combustion

2020 ◽  
Author(s):  
George Santos Marinho ◽  
Robson de Farias
Keyword(s):  
Thermal Degradation ◽  
Potassium Carbonate ◽  
Ignition Temperature ◽  
Solid Propellant ◽  
Potassium Nitrate ◽  
Model System ◽  
Propellant Combustion

<p>In the present work, the effects of copper (II) phthalocyanine, CuP (C<sub>32</sub>H<sub>16</sub>CuN<sub>8</sub>) on the combustion of rocket solid propellant is investigated. For this purpose, parameters such as ignition temperature, mass and volume of generated gases are measured. For such purpose, the sucrose-potassium nitrate (KNSu) was employed as a “model system”. It was found that CuP interferes with the combustion of the KNSu propellant, inhibiting the thermal degradation of potassium carbonate and also decreasing the ignition temperature of KNSu. It was identified that, in a percentage of 50%, CuP reduces the ignition temperature of KNSu by ~ 60 ºC.</p>

Copper (II) Phthalocyanine Effects On Solid Propellant Combustion

2020 ◽  
Author(s):  
George Santos Marinho ◽  
Robson de Farias
Keyword(s):  
Thermal Degradation ◽  
Potassium Carbonate ◽  
Ignition Temperature ◽  
Solid Propellant ◽  
Potassium Nitrate ◽  
Model System ◽  
Propellant Combustion

<p>In the present work, the effects of copper (II) phthalocyanine, CuP (C<sub>32</sub>H<sub>16</sub>CuN<sub>8</sub>) on the combustion of rocket solid propellant is investigated. For this purpose, parameters such as ignition temperature, mass and volume of generated gases are measured. For such purpose, the sucrose-potassium nitrate (KNSu) was employed as a “model system”. It was found that CuP interferes with the combustion of the KNSu propellant, inhibiting the thermal degradation of potassium carbonate and also decreasing the ignition temperature of KNSu. It was identified that, in a percentage of 50%, CuP reduces the ignition temperature of KNSu by ~ 60 ºC.</p>

scholarly journals Optimization Study of the Solid Propellant (Rocket Fuel) Based on Extracted Bitumen of Indonesian Natural Buton Asphalt

2014 ◽  
Vol 13 (2) ◽  
pp. 57
Author(s):  
Bardi Murachman ◽  
Sajono Sajono ◽  
Fauzan Afandi ◽  
Johan Khaeri
Keyword(s):  
Solid Propellant ◽  
Average Rate ◽  
Specific Impulse ◽  
Potassium Nitrate ◽  
Operating Conditions ◽  
Optimum Operating ◽  
Ignition Process ◽  
Potassium Perchlorate ◽  
Advantages And Disadvantages ◽  
Optimization Study

The asphalt propellant for rockets has been investigated since 1960. This material has been developed with the variation of fuels, oxidizer, binders, metal elements and additives. As solid propellant, it has some advantages and disadvantages during the implementation. At present, Extracted Buton asphalt has been studied as an alternative propellant fuels. It is a natural asphalt, extracted from Buton island asphalt rock. When the extract of buton asphalt is mixed with oxidizer, binder, and metal powder, it can be functioned as propellant which is able to release high intensity of energy, have strong thrust and power to fly the rocket. This optimization study of solid propellant was conducted by mixing the Buton asphalt as fuel, oxidizer, metal element and other additives to form a solid propellant. The oxidizer consisted of potassium nitrate (KNO3) and potassium perchlorate (KClO4). The variations of KClO4/KNO3, propellant density and the ratio of the nozzle diameter were also conducted in order to find the best propellant composition and the optimum operating conditions to produce enough power while maintain the integrity of the rocket. The main parameters such as the propellant’s thrust (F) and the specific impulse (Isp) were examined. The results showed that higher composition of KClO4/KNO3 gave the higher value of the thrust and the specific impulse. KClO4/KNO3 levels above the 1:1 ratio produced an explosive properties at the time of ignition. The tendency of propellant to explode during ignition process was also observed. The optimum condition was obtained at the KClO4/KNO3 ratio of 1:1 , the propellant density was 1.900 gram/cm3 and Ae/A* was 3.33. These conditions generated impulse value that last for 277.07 seconds, average thrust of 14.082 N, and average rate of combustion of 0,24 cm/second. Therefore, it can be concluded that propellant with fuel from extracted of Buton asphalt can be used as an alternative propellant for rocket.

Ultrastructural investigation of spontaneous pituitary gonadotroph cell adenomas in aging Sprague-Dawley rats

1983 ◽  
Vol 41 ◽  
pp. 702-703
Author(s):  
D. J. McComb ◽  
J. Beri ◽  
F. Zak ◽  
K. Kovacs
Keyword(s):  
Electron Microscopy ◽  
Animal Model ◽  
Epoxy Resin ◽  
Immunoelectron Microscopy ◽  
Tumor Type ◽  
Gonadal Function ◽  
Sprague Dawley ◽  
Male And Female ◽  
Reticulin Fibers ◽  
Sprague Dawley Rats

Gonadotroph cell adenomas of the pituitary are infrequent in human patients and are not invariably associated with altered gonadal function. To date, no animal model of this tumor type exists. Herein, we describe spontaneous gonadotroph cell adenomas in old male and female Sprague-Dawley rats by histology, immunocytology and electron microscopy.The material consisted of the pituitaries of 27 male and 38 female Sprague Dawley rats, all 26 months of age or older, removed at routine autopsy. Sections of formal in-fixed, paraffin-embedded tissue were stained with hematoxylin-phloxine-saffron (HPS), the PAS method and the Gordon-Sweet technique for the demonstration of reticulin fibers. For immunostaining, sections were exposed to anti-rat β-LH, anti-ratβ-TSH, anti-rat PRL, anti-rat GH and anti-rat ACTH 1-39. For electron microscopy, tissue was fixed in 2.5% glutaraldehyde, postfixed in 1% OsO4 and embedded in epoxy-resin. Tissue fixed in 10% formalin, embedded in epoxy resin without osmification, was used for immunoelectron microscopy.

Surface Structure in Microtomed Sections Caused by Glass and Diamond Knives

1971 ◽  
Vol 29 ◽  
pp. 456-457
Author(s):  
J. Temple Black ◽  
William G. Boldosser
Keyword(s):  
Plastic Deformation ◽  
Epoxy Resin ◽  
Carbon Coating ◽  
Surface Damage ◽  
Body Angle ◽  
Normal Manner ◽  
Bottom Side ◽  
Cutting Direction ◽  
Made In ◽  
Diamond Knife

Ultramicrotomy produces plastic deformation in the surfaces of microtomed TEM specimens which can not generally be observed unless special preparations are made. In this study, a typical biological composite of tissue (infundibular thoracic attachment) infiltrated in the normal manner with an embedding epoxy resin (Epon 812 in a 60/40 mixture) was microtomed with glass and diamond knives, both with 45 degree body angle. Sectioning was done in Portor Blum Mt-2 and Mt-1 microtomes. Sections were collected on formvar coated grids so that both the top side and the bottom side of the sections could be examined. Sections were then placed in a vacuum evaporator and self-shadowed with carbon. Some were chromium shadowed at a 30 degree angle. The sections were then examined in a Phillips 300 TEM at 60kv.Carbon coating (C) or carbon coating with chrom shadowing (C-Ch) makes in effect, single stage replicas of the surfaces of the sections and thus allows the damage in the surfaces to be observable in the TEM. Figure 1 (see key to figures) shows the bottom side of a diamond knife section, carbon self-shadowed and chrom shadowed perpendicular to the cutting direction. Very fine knife marks and surface damage can be observed.

Epoxy Resin Embedment

1968 ◽  
Vol 26 ◽  
pp. 100-101
Author(s):  
J. G. Adams ◽  
M. M. Campbell ◽  
H. Thomas ◽  
J. J. Ghldonl
Keyword(s):  
Electron Microscopy ◽  
Electron Beam ◽  
Epoxy Resin ◽  
Light Microscope ◽  
Epoxy Resins ◽  
Image Contrast ◽  
Tissue Preservation ◽  
Resin System ◽  
Excellent Quality

Since the introduction of epoxy resins as embedding material for electron microscopy, the list of new formulations and variations of widely accepted mixtures has grown rapidly. Described here is a resin system utilizing Maraglas 655, Dow D.E.R. 732, DDSA, and BDMA, which is a variation of the mixtures of Lockwood and Erlandson. In the development of the mixture, the Maraglas and the Dow resins were tested in 3 different volumetric proportions, 6:4, 7:3, and 8:2. Cutting qualities and characteristics of stability in the electron beam and image contrast were evaluated for these epoxy mixtures with anhydride (DDSA) to epoxy ratios of 0.4, 0.55, and 0.7. Each mixture was polymerized overnight at 60°C with 2% and 3% BDMA.Although the differences among the test resins were slight in terms of cutting ease, general tissue preservation, and stability in the beam, the 7:3 Maraglas to D.E.R. 732 ratio at an anhydride to epoxy ratio of 0.55 polymerized with 3% BDMA proved to be most consistent. The resulting plastic is relatively hard and somewhat brittle which necessitates trimming and facing the block slowly and cautiously to avoid chipping. Sections up to about 2 microns in thickness can be cut and stained with any of several light microscope stains and excellent quality light photomicrographs can be taken of such sections (Fig. 1).

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