Bibliografie tematiche / Burning rate

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Letteratura scientifica selezionata sul tema "Burning rate"

Autore: Grafiati
Pubblicato: 4 giugno 2021
Ultima modifica: 29 aprile 2023

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Articoli di riviste sul tema "Burning rate"

1

Atwood, A. I., T. L. Boggs, P. O. Curran, T. P. Parr, D. M. Hanson-Parr, C. F. Price e J. Wiknich. "Burning Rate of Solid Propellant Ingredients, Part 2: Determination of Burning Rate Temperature Sensitivity". Journal of Propulsion and Power 15, n. 6 (novembre 1999): 748–52. http://dx.doi.org/10.2514/2.5523.

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2

Doriath, G. "HIGH BURNING RATE SOLID ROCKET PROPELLANTS". International Journal of Energetic Materials and Chemical Propulsion 4, n. 1-6 (1997): 646–60. http://dx.doi.org/10.1615/intjenergeticmaterialschemprop.v4.i1-6.610.

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3

Kubota, N., T. Sonobe, A. Yamamoto e H. Shimizu. "Burning rate characteristics of GAP propellants". Journal of Propulsion and Power 6, n. 6 (novembre 1990): 686–89. http://dx.doi.org/10.2514/3.23273.

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4

Lipatnikov, A. N. "Burning Rate in Impinging Jet Flames". Journal of Combustion 2011 (2011): 1–11. http://dx.doi.org/10.1155/2011/737914.

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A method for evaluating burning velocity in premixed turbulent flames stabilized in divergent mean flows is quantitatively validated using numerical approximations of measured axial profiles of the mean combustion progress variable, mean and conditioned axial velocities, and axial turbulent scalar flux, obtained by four research groups from seven different flames each stabilized in an impinging jet. The method is further substantiated by analyzing the combustion progress variable balance equation that is yielded by the extended Zimont model of premixed turbulent combustion. The consistency of the model with the aforementioned experimental data is also demonstrated.
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5

Zain-ul-Abdin, Zain-ul-Abdin, Li Wang, Haojie Yu, Muhammad Saleem, Muhammad Akram, Nasir M. Abbasi, Hamad Khalid, Ruoli Sun e Yongsheng Chen. "Ferrocene-based polyethyleneimines for burning rate catalysts". New Journal of Chemistry 40, n. 4 (2016): 3155–63. http://dx.doi.org/10.1039/c5nj03171k.

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6

MIZUNO, TOMOYUKI. "BURNING BEHAVIOUR OF UPHOLSTERED FURNITURE IN FIRE TEST : Part 1 Burning rate". Journal of Structural and Construction Engineering (Transactions of AIJ) 363 (1986): 103–9. http://dx.doi.org/10.3130/aijsx.363.0_103.

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7

Rashkovskiy, S. A., V. G. Krupkin e V. N. Marshakov. "Burning rate of solid homogeneous energetic materials with a curved burning surface". Journal of Physics: Conference Series 1250 (giugno 2019): 012041. http://dx.doi.org/10.1088/1742-6596/1250/1/012041.

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8

LI, Jing, Toshimi TAKAGI, Tatsuyuki OKAMOTO e Shinichi KINOSHITA. "Flame Structure, Burning Velocity and Burning Rate in Stretch Controlled Premixed Flame". Transactions of the Japan Society of Mechanical Engineers Series B 70, n. 691 (2004): 767–72. http://dx.doi.org/10.1299/kikaib.70.767.

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9

Krishnan, S., e R. Jeenu. "Subatmospheric burning charaterristics of AP/CTPB composite propellants with burning rate modifiers". Combustion and Flame 80, n. 1 (aprile 1990): 1–6. http://dx.doi.org/10.1016/0010-2180(90)90048-v.

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10

Tahsini, Amir Mahdi. "Regression rate response in spin-stabilized solid fuel ramjets". Journal of Mechanics 37 (2020): 37–43. http://dx.doi.org/10.1093/jom/ufaa012.

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ABSTRACT The regression rate of the solid fuel in the spinning solid fuel ramjet is investigated here using numerical simulations. The finite volume solver of the reacting turbulent flow is developed to study the flow field in the back-step combustion chamber where the burning rate of the solid fuel is computed using the conjugate heat transfer. The dependence of the burning rate on the circumferential velocity of the ramjet is studied, and it is shown that the spin augments the burning rate due to the enhancement of the convective heat flux along the fuel grain. So, the spin can be used to improve the performance of the solid fuel ramjets. In addition, the effect of rapid change in spin velocity on the regression rate of the fuel is investigated, which shows the transient-burning behavior. The results show that although the spin may increase the burning rate by ∼10% in steady-state operation of the ramjet, the spin acceleration may cause the overshoot in burning rate with the peak value >30% in the unsteady operation.
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Più fonti

Tesi sul tema "Burning rate"

1

Acikalin, Serdar. "Synthesis Of Ferrocenyl Quinones And Ferrocenyl Based Burning Rate Catalysts". Master's thesis, METU, 2003. http://etd.lib.metu.edu.tr/upload/1081256/index.pdf.

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Recently, considerable interest has been devoted to the synthesis of new ferrocene derivatives since properly functionalized ferrocene derivatives could be potential antitumor substances. For this purpose, we have investigated the synthesis of ferrocenyl quinones starting from squaric acid. Thermolysis of ferrocenylsubstituted cyclobutenones, which have been prepared from ferrocenyl cyclobutenediones and alkenyllithiums, affords hydroquinones, which furnish, upon oxidation, ferrocenyl quinones. Ferrocenyl cyclobutenediones have been prepared from known cyclobutenediones by nucleophilic addition of ferrocenyllithiumfollowed by hydrolysis, Pd/Cu-cocatalyzed cross-coupling with (tri-n-butylstannyl)ferrocene or Friedel&
#8211
Crafts alkylation with ferrocene. A mechanism involving electrocyclic ring opening of alkenyl substituted cyclobutenone to dienylketene and consequent electrocyclic ring closure to cyclohexadienone followed by enolization has been proposed to account for the formation of ferocenyl substituted hydroquinones. Rocket design and production is one of the hottest topics in defense industry. On this subject, significant amount of investments have been done and excellent results were obtained. Among the burning rate catalysts for composite rocket propellants, ferrocene derivatives are one of the most famous ones. Although ferrocene derivatives are superior to some other burning rate catalysts, their use has some drawbacks arising from the tendency of migration in the bulk of the material and their sensitivity toward oxidation by air. With the aim of preventing the negative aspects of ferrocene derivatives, we have investigated the synthesis of EDA (ethylenediamine), TEP (tetraethylenepentamine) and DDI (dimeryl-diisocyanate) based ferrocene derivatives.
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2

Bellino, Peter William. "A Study of Spreading and In Situ Burning of Oil in an Ice Channel". Digital WPI, 2012. https://digitalcommons.wpi.edu/etd-theses/1172.

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The potential for oil exploration on the Arctic Outer Continental Shelf warrants determination of an efficient method to clean up an oil spill. Traditional spill response equipment may not be practical in an Arctic environment; the presence of ice which may prevent proper deployment of equipment. The remoteness of the areas proposed for oil exploration lack the infrastructure and support networks necessary to stage a response to a large oil spill. These difficulties make it necessary to explore alternative means of oil spill cleanup. In situ burning is one method that may be particularly well-suited for arctic and sub-arctic environments due to the minimal amount of equipment required to achieve an efficient burn, i.e. high mass loss. The Arctic and sub- Arctic environments add an additional level of complexity by introducing a spill medium (ice) that is highly unstable at elevated temperatures. Our experiments sought to calculate the mass loss rate of oil mixtures to determine the efficiency with which they burn within ice channels of varying widths. Since fuel layer thickness is a critical factor in determining the effectiveness of an in situ burn the spread rate of oil along an ice channel was studied. Burning of oil in an ice channel yields low efficiencies (10%) primarily due to the geometric changes of the melting ice channel. The spreading was modeled as a constant flux rectilinear buoyancy-inertia governed flow. The melting causes an increase in the surface area and results in the critical thickness of the oil to be reached sooner. Based on the current bench- scale testing, losses due to ice melting cause the efficiencies of the burning process to be excessively low and not viable to full scale clean up. The results warrant future research to understand how varying other parameters, including starting mass of fuel, influence efficiencies.
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3

Farmahini, Farahani Hamed. "A Study on Burning of Crude Oil in Ice Cavities". Digital WPI, 2014. https://digitalcommons.wpi.edu/etd-theses/501.

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Abstract (sommario):
In situ burning (ISB) is a practical method of oil spill cleanup in icy conditions. This study investigates one example of a likely oil spill scenario; burning oil in an ice cavity. In this situation, unique and unexplored physical processes come into play compared with the classical problem of confined pool fires in vessels. The icy walls of the cavity create a significant heat sink causing notable lateral heat losses especially for small cavity sizes (5-10 cm). Melting of ice because of the heat from the flame causes the geometry of cavity to change. Specifically, the diameter of the pool fire increases as the burning advances. This widening causes the fuel to stretch laterally thereby reducing its thickness at a faster rate. The melted ice water causes the oil layer to rise which causes the ullage height to decrease. The decrease in ullage and increase in diameter counteract the reduction in thickness because of widening or stretching of the fuel layer. There thus exists a strong coupling between the burning rate and the geometry change of the pool and cavity. To explore the problem, experiments were performed in circular ice cavities of varying diameters (5 - 25 cm). The change in shape of the ice cavity and the oil layer thickness are recorded using a combination of visual images, mass loss, and temperature data along the centerline and edge of the cavity. The average burning rate of crude oil in a cavity is greater than the corresponding burning rate in a vessel of equal diameter, yet the burning efficiency (% of fuel consumed during combustion) is lower. For example, the average mass loss rate in a 10 cm ice cavity is 50% higher than a steel vessel of similar size. However, the burning efficiency is lower by 50%. Widening of cavity (170%) contributes to the increase in the average mass burning rate. At the same time heat losses through fuel layer increase because of decrease in fuel thickness by widening of the fuel layer. This coupling is analyzed using a mathematical model which can predict burning rate and efficiency of crude oil in an ice cavity for the range of cavity diameters examined. Extension of the model to larger sizes comparable to realistic situations in the Arctic is discussed.
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4

Ward, Nicholas Rhys. "The rate-limiting mechanism for the heterogeneous burning of iron in normal gravity and reduced gravity". Queensland University of Technology, 2007. http://eprints.qut.edu.au/16673/.

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This thesis presents a research project in the field of oxygen system fire safety relating to the heterogeneous burning of iron in normal gravity and reduced gravity. Fires involving metallic components in oxygen systems often occur, with devastating and costly results, motivating continued research to improve the safety of these devices through a better understanding of the burning phenomena. Metallic materials typically burn in the liquid phase, referred to as heterogeneous burning. A review of the literature indicates that there is a need to improve the overall understanding of heterogeneous burning and better understand the factors that influence metal flammability in normal gravity and reduced gravity. Melting rates for metals burning in reduced gravity have been shown to be higher than those observed under similar conditions in normal gravity, indicating that there is a need for further insight into heterogeneous burning, especially in regard to the rate-limiting mechanism. The objective of the current research is to determine the cause of the higher melting rates observed for metals burning in reduced gravity to (a) identify the rate-limiting mechanism during heterogeneous burning and thus contribute to an improved fundamental understanding of the system, and (b) contribute to improved oxygen system fire safety for both ground-based and space-based applications. In support of the work, a 2-s duration ground-based drop tower reduced-gravity facility was commissioned and a reduced-gravity metals combustion test system was designed, constructed, commissioned and utilised. These experimental systems were used to conduct tests involving burning 3.2-mm diameter cylindrical iron rods in high-pressure oxygen in normal gravity and reduced gravity. Experimental results demonstrate that at the onset of reduced gravity, the burning liquid droplet rapidly attains a spherical shape and engulfs the solid rod, and that this is associated with a rapid increase in the observed melting rate. This link between the geometry of the solid/liquid interface and melting rate during heterogeneous burning is of particular interest in the current research. Heat transfer analysis was performed and shows that a proportional relationship exists between the surface area of the solid/liquid interface and the observed melting rate. This is confirmed through detailed microanalysis of quenched samples that shows excellent agreement between the proportional change in interfacial surface area and the observed melting rate. Thus, it is concluded that the increased melting rates observed for metals burning in reduced gravity are due to altered interfacial geometry, which increases the contact area for heat transfer between the liquid and solid phases. This leads to the conclusion that heat transfer across the solid/liquid interface is the rate-limiting mechanism for melting and burning, limited by the interfacial surface area. This is a fundamental result that applies in normal gravity and reduced gravity and clarifies that oxygen availability, as postulated in the literature, is not rate limiting. It is also established that, except for geometric changes at the solid/liquid interface, the heterogeneous burning phenomenon is the same at each gravity level. A conceptual framework for understanding and discussing the many factors that influence heterogeneous burning is proposed, which is relevant to the study of burning metals and to oxygen system fire safety in both normal-gravity and reduced-gravity applications.
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5

Ward, Nicholas Rhys. "The rate-limiting mechanism for the heterogeneous burning of iron in normal gravity and reduced gravity". Thesis, Queensland University of Technology, 2007. https://eprints.qut.edu.au/16673/1/Nicholas_Ward_Thesis.pdf.

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Abstract (sommario):
This thesis presents a research project in the field of oxygen system fire safety relating to the heterogeneous burning of iron in normal gravity and reduced gravity. Fires involving metallic components in oxygen systems often occur, with devastating and costly results, motivating continued research to improve the safety of these devices through a better understanding of the burning phenomena. Metallic materials typically burn in the liquid phase, referred to as heterogeneous burning. A review of the literature indicates that there is a need to improve the overall understanding of heterogeneous burning and better understand the factors that influence metal flammability in normal gravity and reduced gravity. Melting rates for metals burning in reduced gravity have been shown to be higher than those observed under similar conditions in normal gravity, indicating that there is a need for further insight into heterogeneous burning, especially in regard to the rate-limiting mechanism. The objective of the current research is to determine the cause of the higher melting rates observed for metals burning in reduced gravity to (a) identify the rate-limiting mechanism during heterogeneous burning and thus contribute to an improved fundamental understanding of the system, and (b) contribute to improved oxygen system fire safety for both ground-based and space-based applications. In support of the work, a 2-s duration ground-based drop tower reduced-gravity facility was commissioned and a reduced-gravity metals combustion test system was designed, constructed, commissioned and utilised. These experimental systems were used to conduct tests involving burning 3.2-mm diameter cylindrical iron rods in high-pressure oxygen in normal gravity and reduced gravity. Experimental results demonstrate that at the onset of reduced gravity, the burning liquid droplet rapidly attains a spherical shape and engulfs the solid rod, and that this is associated with a rapid increase in the observed melting rate. This link between the geometry of the solid/liquid interface and melting rate during heterogeneous burning is of particular interest in the current research. Heat transfer analysis was performed and shows that a proportional relationship exists between the surface area of the solid/liquid interface and the observed melting rate. This is confirmed through detailed microanalysis of quenched samples that shows excellent agreement between the proportional change in interfacial surface area and the observed melting rate. Thus, it is concluded that the increased melting rates observed for metals burning in reduced gravity are due to altered interfacial geometry, which increases the contact area for heat transfer between the liquid and solid phases. This leads to the conclusion that heat transfer across the solid/liquid interface is the rate-limiting mechanism for melting and burning, limited by the interfacial surface area. This is a fundamental result that applies in normal gravity and reduced gravity and clarifies that oxygen availability, as postulated in the literature, is not rate limiting. It is also established that, except for geometric changes at the solid/liquid interface, the heterogeneous burning phenomenon is the same at each gravity level. A conceptual framework for understanding and discussing the many factors that influence heterogeneous burning is proposed, which is relevant to the study of burning metals and to oxygen system fire safety in both normal-gravity and reduced-gravity applications.
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6

Arvanetes, Jason. "DESIGN AND IMPLEMENTATION OF AN EMISSION SPECTROSCOPY DIAGNOSTIC IN A HIGH-PRESSURE STRAND BURNER FOR THE STUDY OF SOLID PROPELL". Master's thesis, University of Central Florida, 2006. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/2820.

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The application of emission spectroscopy to monitor combustion products of solid rocket propellant combustion can potentially yield valuable data about reactions occurring within the volatile environment of a strand burner. This information can be applied in the solid rocket propellant industry. The current study details the implementation of a compact spectrometer and fiber optic cable to investigate the visible emission generated from three variations of solid propellants. The grating was blazed for a wavelength range from 200 to 800 nm, and the spectrometer system provides time resolutions on the order of 1 millisecond. One propellant formula contained a fine aluminum powder, acting as a fuel, mixed with ammonium perchlorate (AP), an oxidizer. The powders were held together with Hydroxyl-Terminated-Polybutadiene (HTPB), a hydrocarbon polymer that is solidified using a curative after all components are homogeneously mixed. The other two propellants did not contain aluminum, but rather relied on the HTPB as a fuel source. The propellants without aluminum differed in that one contained a bimodal mix of AP. Utilizing smaller particle sizes within solid propellants yields greater surface area contact between oxidizer and fuel, which ultimately promotes faster burning. Each propellant was combusted in a controlled, non-reactive environment at a range of pressures between 250 and 2000 psi. The data allow for accurate burning rate calculations as well as an opportunity to analyze the combustion region through the emission spectroscopy diagnostic. It is shown that the new diagnostic identifies the differences between the aluminized and non-aluminized propellants through the appearance of aluminum oxide emission bands. Anomalies during a burn are also verified through the optical emission spectral data collected.
M.S.M.E.
Department of Mechanical, Materials and Aerospace Engineering;
Engineering and Computer Science
Mechanical Engineering
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7

Tanner, Matthew Wilder. "Multidimensional Modeling of Solid Propellant Burning Rates and Aluminum Agglomeration and One-Dimensional Modeling of RDX/GAP and AP/HTPB". Diss., CLICK HERE for online access, 2008. http://contentdm.lib.byu.edu/ETD/image/etd2706.pdf.

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8

Lundell, Carl. "RESEARCH STUDY: REACTING METAL BIS(TRIMETHYL)AMIDES WITH DOUBLE-BASE PROPELLANT STABILIZERS". Master's thesis, Temple University Libraries, 2017. http://cdm16002.contentdm.oclc.org/cdm/ref/collection/p245801coll10/id/437570.

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Chemistry
M.A.
During World War II, it was discovered that when lead was added to double-base propellants, it produced beneficial burn rate phenomena. Specifically, the propellant burn rate first increased unexpectedly at low pressures, then the burn rate became independent of pressure, followed lastly by “mesa burning” where the burn rate actually decreased with increasing pressure. This results in a beneficial negative feedback mechanism. Over the past 75 years, researchers have explored different lead complexes to achieve better propellant performance. However, over the last decade, research has shifted to finding an alternative to using lead as an additive to reduce toxicity. Until the attempts detailed herein, researchers had not, to our knowledge attempted to combine double-base propellant stabilizers with various metals to achieve these desired results. In doing so, we prepared two lead complexes, Tetrakis (µ3-(4-methyl-3-nitrophenyl imido lead (II))) 1, and Bis(dinitrophenyl imido lead(II)) 2, that were synthesized by reacting lead bis(trimethylsilyl)amide with a common double-base propellant stabilizer 2-nitrodiphenylamine (NDPA) and 4-methyl-3-nitroaniline. Both complexes formed from protolysis of the trimethylsilylamide ligand by the acidic proton of the amine, and crystallized from tetrahydrofuran (THF). Bomb calorimetry coupled with crystal density structure determined that 1 has a very high energy density of 74.1 MJ/L, more than three times the energy density of conventional nitroamine explosives, whereas 2 was lower at 38.2 MJ/L. The structure, charge and characterization of 1 and 2 are discussed. However, each complex is air sensitive making burn rate experimentation infeasible, so any possible changes to the propellant as an additive remained undetermined. Attempts to use of tin, zinc, or bismuth bis(trimethyl)amides in place of lead, were unsuccessfully characterized, although reactions were likely observed.
Temple University--Theses
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9

Jommi, Alessandro. "Studio e ricostruzione delle distribuzioni granulometriche interne al grano in motori a propellente solido". Master's thesis, Alma Mater Studiorum - Università di Bologna, 2014. http://amslaurea.unibo.it/7829/.

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The main purposes of this essay were to investigate in detail the burning rate anomaly phenomenon, also known as "Hump Effect", in solid rocket motors casted in mandrel and the mechanisms at the base of it, as well as the developing of a numeric code, in Matlab environment, in order to obtain a forecasting tool to generate concentration and orientation maps of the particles within the grain. The importance of these analysis is due to the fact that the forecasts of ballistics curves in new motors have to be improved in order to reduce the amount of experimental tests needed for the characterization of their ballistic behavior. This graduate work is divided into two parts. The first one is about bidimensional and tridimensional simulations on z9 motor casting process. The simulations have been carried out respectively with Fluent and Flow 3D. The second one is about the analysis of fluid dynamic data and the developing of numeric codes which give information about the concentration and orientation of particles within the grain based on fluid strain rate information which are extrapolated from CFD software.
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10

Gabriel, Vladimir Hallak. "Estudo de modificadores balísticos na formulação de propelentes base dupla visando à otimização de sua velocidade de queima". Universidade de São Paulo, 2014. http://www.teses.usp.br/teses/disponiveis/97/97137/tde-30042014-094502/.

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Propelentes sólidos são materiais energéticos que produzem gases em alta pressão por meio de uma reação de combustão. Qualquer propelente sólido inclui dois ou mais dos seguintes componentes: oxidante (nitratos e percloratos); combustível (resinas orgânicas ou polímeros); compostos químicos combinando oxidantes e combustíveis (nitrocelulose ou nitroglicerina); aditivos para facilitar processos de produção ou alterar a taxa de queima e inibidores (fita de etilcelulose), para restringir superfícies de combustão. Pequenas percentagens de aditivos são usadas para modificar diversas propriedades mecânicas, químicas e balísticas dos propelentes sólidos: acelerar ou desacelerar a velocidade de combustão (catalisadores e inibidores de combustão, respectivamente); assegurar a estabilidade química para prevenir a deterioração durante a estocagem; controlar as propriedades de processamento durante a produção de propelente (tempo de cura, fluidez para extrusão ou moldagem, etc.); controlar as propriedades de absorção de radiação no propelente em combustão; aumentar a resistência mecânica e diminuir a deformação elástica; e, finalmente, minimizar a sensibilidade térmica. No caso de propelentes sólidos Base Dupla (mistura de duas bases ativas: a nitrocelulose e a nitroglicerina), é possível alterar sua velocidade de queima principalmente pelo emprego de pequenos teores de modificadores balísticos, em geral sais orgânicos de cobre e chumbo. Neste trabalho, estudou-se a aceleração da velocidade de queima de uma formulação conhecida de propelente Base Dupla - BD, alterando o teor total dos modificadores balísticos cromato de cobre e estearato de chumbo (ou plastabil - nome comercial) na receita original, bem como a proporção entre eles. Estas alterações na formulação original devem, idealmente, preservar os parâmetros de desempenho estabelecidos para as propriedades químicas (estabilidade química) e mecânicas (densidade da massa e ensaios de tração), ao mesmo tempo otimizando o desempenho balístico, pelo aumento da velocidade de queima. Os resultados experimentais mostram que para os parâmetros de qualidade elongação e velocidade de queima a interação entre os fatores, Proporção Sal de Chumbo/Sal de Cobre (Fator A) e Teor de Modificadores Balísticos (Fator B) foram significativos, ou seja, quanto maior os fatores pior o resultado com as propriedades. Com os parâmetros de resistência a tração e densidade da massa, o fator A e B respectivamente influenciam negativamente quando aumentado em sua concentração. Para o parâmetro estabilidade química não houve nenhum sinal de melhora ou influencia dos fatores. No caso da velocidade de queima a interação AB é o que mais influencia. Melhorando significativamente a velocidade de queima.
Solid propellants are energetic materials which produce a considerable amount of high-pressure gases by means of a combustion reaction. Any solid propellant formulation includes at least two of the following items: oxidizer (nitrates and perchlorates); fuel (organic resins or polymers); chemical compounds combining oxidizers and fuels (nitrocellulose or nitroglycerine); additives to easy production operations or to modify the burning rate and inhibitors (tape ethyl-cellulose), to restrict the combustion surfaces. Small amounts of additives are employed to modify the mechanical, chemical and ballistic features of the solid propellants: to accelerate or diminish the burning rate (catalysts and inhibitors of burning, respectively); to assure the chemical stability in order to prevent the deterioration during stocking; to control the processing properties during propellant production (curing time, extrusion or casting rheology); to control the radiation absorption in the burning propellant; to enhance the mechanical resistance and to reduce the strain; and, finally, to get the thermal sensitivity to a minimum level. In the case of Double-Base solid propellants (blend of two energetic bases: nitrocellulose and nitroglycerine), it\'s possible to control its burning rate mainly by the use of small amounts of ballistic modifiers, generally copper and lead organic salts. This work has studied the burning rate acceleration of a known Double-Base propellant formulation, by changing the total amount of the ballistic modifiers copper chromate and lead stearate (commercially known as plastabil) in the original formulation, as well as the proportion between them. These changes at the original recipe should preserve, ideally, the performance levels required for the chemical (chemical stability) and mechanical properties (density and stress-strain evaluation), optimizing, at the same time, the ballistic performance, through the burning rate enhancement. Results show that for the parameters of quality and elongation rate of burning the interaction between factors, Proportion of Lead Salt / Salt Copper (Factor A) and content Ballistic Modifiers (Factor B) were significant, ie, the higher the worst factors result with the properties. With the parameters of tensile strength and mass density, the factor A and B respectively negatively influence increased when its concentration. For the chemical stability parameter there was no sign of improvement or influences of factors. In the case of burning rate AB interaction is what most influences. Significantly improving the speed of burning.
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Più fonti

Libri sul tema "Burning rate"

1

Xiao, W. Application of burning rate identification technique. Washington, D. C: American Institute of Aeronautics and Astronautics, 1989.

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2

Glick, Robert L. On the reduction of high pressure ballistic data. Washington, D. C: American Institute of Aeronautics and Astronautics, 1986.

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3

Baer, Paul G. Simulation of close chamber burning of very-high burning rate propellant. Aberdeen Proving Ground, Md: Ballistic Research Laboratory, 1988.

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4

White, Kevin J. Closed chamber burning characteristics of new VHBR formulations. Aberdeen Proving Ground, Md: Ballistic Research Laboratory, 1985.

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5

Tisdall, Grant W. C. A numerical model of reactive gas-particulate complex turbulent flow in a constant volume vessel. [Toronto, Ont.]: Dept. of Aerospace Science and Engineering, University of Toronto, 1992.

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6

Glick, Robert L. An improved closed burner method. New York: American Institute of Aeronautics and Astronautics, 1990.

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7

United States. National Aeronautics and Space Administration., a cura di. Explicit expression to predict the erosive burning rate of solid propellants. Washington DC: National Aeronautics and Space Administration, 1986.

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Berger, F. C. Heat transfer from propellant burning in a constant-volume chamber. [Downsview, Ont.]: Department of Aerospace Science and Engineering, University of Toronto, 1990.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Combustion of solid propellants. Neuilly sur Seine, France: AGARD, 1991.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Combustion of solid propellants. Neuilly sur Seine, France: AGARD, 1991.

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Capitoli di libri sul tema "Burning rate"

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Viegas, Domingos X., C. Pinto e J. Raposo. "Burning Rate". In Encyclopedia of Wildfires and Wildland-Urban Interface (WUI) Fires, 1–8. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-51727-8_50-1.

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Viegas, Domingos X., C. Pinto e J. Raposo. "Burning Rate". In Encyclopedia of Wildfires and Wildland-Urban Interface (WUI) Fires, 68–74. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-319-52090-2_50.

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Isert, Sarah, e Steven F. Son. "The Relationship Between Flame Structure and Burning Rate for Ammonium Perchlorate Composite Propellants". In Challenges and Advances in Computational Chemistry and Physics, 171–211. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-59208-4_6.

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Roth, N., K. Anders e A. Frohn. "Experimental Investigation of the Reduction of Burning Rate Due to Finite Spacing Between Droplets". In Aerothermodynamics in Combustors, 175–83. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-84755-4_12.

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Gooch, Jan W. "Burning Rates". In Encyclopedic Dictionary of Polymers, 99. New York, NY: Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4419-6247-8_1690.

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Mezroua, Abderrahmane, Michel H. Lefebvre, Djalal Trache e Kamel Khimeche. "Burning Rate of PVC—Plastisol Composite Propellants and Correlation Between Closed Vessel and Strand Burner Tests Data". In Innovative Energetic Materials: Properties, Combustion Performance and Application, 351–72. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-4831-4_12.

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Trivedi, Shrey, Girish V. Nivarti e R. Stewart Cant. "Analysis of Flame Topology and Burning Rates". In Data Analysis for Direct Numerical Simulations of Turbulent Combustion, 1–17. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-44718-2_1.

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Sikdar, Debosmita, Ivy Kanungo e Dipanwita Das. "Microbial Enzymes: A Summary Focusing on Biotechnology Prospective for Combating Industrial Pollutants". In Proceedings of the Conference BioSangam 2022: Emerging Trends in Biotechnology (BIOSANGAM 2022), 70–76. Dordrecht: Atlantis Press International BV, 2022. http://dx.doi.org/10.2991/978-94-6463-020-6_8.

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AbstractEnvironmental issues are growing at an alarming rate and addressing the same is the need of the hour. Hazardous industrial pollutants and discharges are adding to the misery. Therefore, new ideas and technologies are being created and adopted to deal with ever increasing conservational troubles. Due to the burning issue of environmental pollution rising daily, a paradigm shift towards more sustainable and greener has to be pondered on. Microbial enzymes are such versatile, useful and beneficial weapons those can be exploited to combat the above-mentioned issues. In this aspect various works have been done and different sources of isolation of microbes and their fermentation process for procuring enzymes from them have been investigated in detail in those work. Pualsa Jagdish et al.’s work (2013) from Viva College, Virar, and Maharashtra entails that Lipase enzyme was procured from curd and waste oil was used as substrate. Lipase was produced by Lactobacillus sp. Whose lipolytic activity was calculated to be 0.082 U/mg. This enzyme if isolated under favorable conditions can be used to be applied for various industrial purposes in order to suppress the pollution rate and reduced the dependency on market-based chemicals and reagents those are highly dangerous and harmful. Work of Ashutosh Nema et al. (2019) [1], talks about the use of lipase enzyme as well as proteases are used as catalysts in biodiesel production as an effective and economical approach. According to Wu et al., large scale productions of protease have been achieved from Aspergillus species for their application in food and beverage industries. Alkaline proteases were reported to be produced under solid state fermentation processes by A. flavus and A. oryzae. Ikram-Ul-Haq and Mukhtar (2015) [2] stated that Penicillium sp. Alkaline proteases were generated under both solid state and submerged fermentation. The Mucor sp. of fungi can produce protease for milk clotting and can substitute rennin in the cheese making industry. Fungal enzymes are commonly used in industries over bacterial enzymes due to various technical reasons such as the feasibility of gaining enzymes at a high concentration in the fermentation medium and easier downstream processing. This way it can be encapsulated that microbial enzymes are savior in the field of pollution remediation and replacer of harsh and hazardous chemicals for carrying out various industrial applications.
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Vanbeveren, D. "The Influence of WR like Stellar Wind Mass Loss Rates on the Evolution of Massive Core Helium Burning Stars". In Wolf-Rayet Stars and Interrelations with other Massive Stars in Galaxies, 555. Dordrecht: Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3306-7_103.

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Goulding, Keith, T. Scott Murrell, Robert L. Mikkelsen, Ciro Rosolem, Johnny Johnston, Huoyan Wang e Marta A. Alfaro. "Outputs: Potassium Losses from Agricultural Systems". In Improving Potassium Recommendations for Agricultural Crops, 75–97. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-59197-7_3.

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Abstract (sommario):
AbstractPotassium (K) outputs comprise removals in harvested crops and losses via a number of pathways. No specific environmental issues arise from K losses to the wider environment, and so they have received little attention. Nevertheless, K is very soluble and so can be leached to depth or to surface waters. Also, because K is bound to clays and organic materials, and adsorbed K is mostly associated with fine soil particles, it can be eroded with particulate material in runoff water and by strong winds. It can also be lost when crop residues are burned in the open. Losses represent a potential economic cost to farmers and reduce soil nutritional status for plant growth. The pathways of loss and their relative importance can be related to: (a) the general characteristics of the agricultural ecosystem (tropical or temperate regions, cropping or grazing, tillage management, interactions with other nutrients such as nitrogen); (b) the specific characteristics of the agricultural ecosystem such as soil mineralogy, texture, initial soil K status, sources of K applied (organic, inorganic), and rates and timing of fertilizer applications. This chapter provides an overview of the main factors affecting K removals in crops and losses through runoff, leaching, erosion, and open burning.
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Atti di convegni sul tema "Burning rate"

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Glick, Robert, Richard Hessler e Luigi DeLuca. "Acceleration Augmented Burning Rate Data". In 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-3866.

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GONTHIER, B., e J. TAUZIA. "Burning rate enhancement phenomena in end-burning solid propellant grains". In 21st Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-1435.

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Uyehara, Otto A. "Sooting, Burning Rate as Influenced by Fuel Structure and Burning Conditions". In SAE International Congress and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1985. http://dx.doi.org/10.4271/850112.

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WINCH, P., e R. IRVINE. "Forced cone burning for active control of solid propellant burning rate". In 22nd Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-1710.

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XIAO, WANG, CHEN BUXUE e WU XINPING. "Application of burning rate identification technique". In 25th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2531.

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KUBOTA, N., T. SONOBE, A. YAMAMOTO e H. SHIMIZU. "Burning rate characteristics of GAP propellants". In 24th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-3251.

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GLICK, ROBERT, e JOHN PIETZ. "Burning rate characterization with progressive motors". In 26th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-1869.

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Lu, Y., E. Boyer, D. Koch, K. Kuo, Y. Lu, E. Boyer, D. Koch e K. Kuo. "Measurement of intrinsic burning rate of nitromethane". In 33rd Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-3107.

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KUBOTA, N., e H. OKUHARA. "Burning rate temperature sensitivity of HMX propellants". In 22nd Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-1593.

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Evans, John, Ashley Penton e Robert Frederick. "Uncertainty of Solid Propellant Burning Rate Measurements". In 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-4975.

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Rapporti di organizzazioni sul tema "Burning rate"

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Fry, R. S., L. DeLuca, R. Frederick, G. Gadiot, R. Strecker, H.-L. Besser, A. Whitehouse, J.-C. Traineau, D. Ribereau e J.-P. Reynaud. Evaluation of Methods for Solid Propellant Burning Rate Measurement. Fort Belvoir, VA: Defense Technical Information Center, gennaio 2002. http://dx.doi.org/10.21236/ada405711.

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Miller, Martin S. Burning-Rate Models and Their Successors: A Personal Perspective. Fort Belvoir, VA: Defense Technical Information Center, giugno 2003. http://dx.doi.org/10.21236/ada416336.

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Robbins, Frederick W., e Theresa Keys. The Burning Rate Behavior of Pure Nitrocellulose Propellant Samples. Fort Belvoir, VA: Defense Technical Information Center, marzo 1993. http://dx.doi.org/10.21236/ada261009.

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Robbins, Frederick W., e David L. Kruczynski. Calculated Gun Interior Ballistic Effects of In-Depth Burning of VHBR (Very High Burning Rate) Propellant. Fort Belvoir, VA: Defense Technical Information Center, novembre 1989. http://dx.doi.org/10.21236/ada214359.

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Shepherd, I. G. Flame surface density and burning rate in premixed turbulent flames. Office of Scientific and Technical Information (OSTI), ottobre 1995. http://dx.doi.org/10.2172/132644.

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Mitler, Henri E. Algorithm for the mass-loss rate of a burning wall. Gaithersburg, MD: National Bureau of Standards, 1987. http://dx.doi.org/10.6028/nbs.ir.87-3682.

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Miller, Martin S., e William R. Anderson. A Chemically Specific Burning Rate Predictor Model for Energetic Materials. Fort Belvoir, VA: Defense Technical Information Center, febbraio 2001. http://dx.doi.org/10.21236/ada392631.

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Quintiere, James G. A semi-quantitative model for the burning rate of solid materials. Gaithersburg, MD: National Institute of Standards and Technology, 1992. http://dx.doi.org/10.6028/nist.ir.4840.

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Fry, Ronald S. Solid Propellant Subscale Burning Rate Test Techniques and Hardware for U.S. and Selected NATO Facilities. Fort Belvoir, VA: Defense Technical Information Center, luglio 2001. http://dx.doi.org/10.21236/ada385431.

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Robbins, Frederick W., e John A. Vanderhoff. A Summary of the JANNAF Workshop on Methods for Exchange of Gun Propellant Burning Rate Information. Fort Belvoir, VA: Defense Technical Information Center, maggio 1993. http://dx.doi.org/10.21236/ada264113.

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