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Chemical Kinetics Of Nitramine Propellant Combustion
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Book Synopsis Chemical kinetics of nitramine propellant combustion by :
Download or read book Chemical kinetics of nitramine propellant combustion written by and published by . This book was released on 1988 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: Many solid rocket propellants and other energetic materials consist of complex chemical compounds of carbon, hydrogen, oxygen and nitrogen. The decomposition of these solid reactants leads to the formation of gaseous hydrocarbons and oxides of nitrogen which can react to support a flame above the surface of the solid. These flames can provide heat which is fed back to the propellant surface and thereby influence the burning rate of the solid. In the case of nitramine based solid rocket propellants, the gas phase decomposition products include significant amounts of Ethyloxide, Hydrogen cyanide, Nitrogen dioxide, Nitric oxide, Nitrous oxide and Oxygen. This study is intended to provide experimental data on the structure of hydrocarbon flames supported by oxides of nitrogen in order to establish the reaction mechanism for such flames. Laminar, premixed, flat flames of Methane/NO2/O2 and CH2O/NO2/O2 have been investigated and a reaction mechanism is suggested which accounts for all of the major observations in the data.
Book Synopsis Chemical Kinetics of Gas Phase Decomposition Products of Nitramine Propellants by : M. C. Branch
Download or read book Chemical Kinetics of Gas Phase Decomposition Products of Nitramine Propellants written by M. C. Branch and published by . This book was released on 1984 with total page 7 pages. Available in PDF, EPUB and Kindle. Book excerpt: Nitramine based solid rocket propellants have the advantages of relatively low infrared and smoke emissions from their exhaust. Although a number of studies have been directed toward chemical and physical processes in the condensed phase during heating or combustion, the understanding of gas phase chemical processes has not been developed. The objective of the studies reported here is to provide additional insight into the chemistry of reactions of gas phase species of importance in the combustion of nitramine propellants. Chemical kinetic modeling of the gas phase reactions is used to evaluate critical reaction paths and energetic and their possible influence on burn rate. Particular attention has been given to the fizz reaction near the propellant surface and the preparation and flame zones standing off the surface. The chemical kinetic modeling shows a two zone behavior which is consistent with previous suggestions about the chemistry of the fizz and flame zones. The first zone is dominated by the rapid between CH20 and NO2 while the second zone results from the slower exothermic reduction of NO.
Book Synopsis Solid Propellant Chemistry Combustion and Motor Interior Ballistics 1999 by : Vigor Yang
Download or read book Solid Propellant Chemistry Combustion and Motor Interior Ballistics 1999 written by Vigor Yang and published by AIAA. This book was released on 2000 with total page 1038 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Nitramine Propellant Ignition and Combustion Research: New Tools and New Directions by :
Download or read book Nitramine Propellant Ignition and Combustion Research: New Tools and New Directions written by and published by . This book was released on 1989 with total page 79 pages. Available in PDF, EPUB and Kindle. Book excerpt: The efficient and successful design of new generations of highly energetic propellants based on evolving nitramine chemistry will require a thorough knowledge of the chemical and physical parameters controlling their ignition and combustion. The necessary level of insight can be attained and successfully embodied in the predictive computer models necessary for effective propellant design, development and testing activities if a coordinated, hierarchical program of theoretical modeling and confirming and supporting experiments is designed and properly executed. This paper reviews the current state of our understanding of the chemistry and physics of nitramine propellant ignition and combustion and develops and motivates the basic research program necessary to put advanced nitramine propellant development on a firm and effective scientific basis. Confronting and solving problems involving complex physicochemical phenomena which intertwine complex heat, mass and radiative transfer processes with chemical kinetics is a challenge which physical and engineering scientists are becoming much more adept at meeting. Modern theoretical and experimental tools are now available which allow the design and utilization of much more comprehensive analytical models as well as their concomitant supporting and confirming experimental measurements. Gun propellants, Rocket propellants, LOVA propellants, Solid propellants, RDX, HMX.
Book Synopsis Combustion Chemistry of Composite Solid Propellants Based on Nitramine and High Energetic Binders by :
Download or read book Combustion Chemistry of Composite Solid Propellants Based on Nitramine and High Energetic Binders written by and published by . This book was released on 2005 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: Chemical and thermal structure of flame of solid propellants based on nitramine (HMX or RDX) and azide polymer (GAP or BAMO-AMMO) has been investigated at pressure of 0.5 and 1.0 MPa by method of molecular-beam mass spectrometry and microthermocouple. Chemical flame structure of pure nitramines at atmospheric pressure has been obtained too. Burning rate has been measured. The probe method of sampling of species from flame allowing to detect products of propellant decomposition (including nitramine vapor) in the zone adjacent to the burning surface has been developed. Eleven species, including nitramine vapor, have been detected in the zone adjacent to the burning surface in the case of nitramine/GAP propellants. Experiments showed that there are two zones of chemical reactions in flame of nitramine/GAP propellants and one zone in flame of nitramine/BAMO-AMMO propellants. Species concentrations have been determined at different distances from the burning surface. Temperature profiles in the combustion wave of solid propellants have been measured. An extensive plateau on the temperature profiles was not observed. Data obtained can be used for creation and validation of combusting model for propellants on the basis of nitramine and azide polymer.
Book Synopsis Ignition, Combustion and Kinetics of Energetic Materials by :
Download or read book Ignition, Combustion and Kinetics of Energetic Materials written by and published by . This book was released on 1998 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: To develop a comprehensive model of nitramine propellant ignition and combustion, the appropriate numerical analysis was developed to solve both transient and steady state combustion, including detailed finite rate chemical kinetics, thermodynamic phase transition, and sub-surface reactions. The model was advanced to predict ignition phenomena. Modeling work was complemented by conducting various experiments. Using fast thermolysis, significant accomplishments were made in studies of the decomposition behavior of propellant ingredients, such as RDX, cellulose acetate butyrate, nitrocellulose, and mixtures of RDX and binders. Intrusive mass spectroscopic techniques were utilized to acquire gas phase species profiles under laser assisted burning of monopropellants and composite propellants. Nonintrusive diagnostic techniques were developed and used to determine temperature and species profiles within propellant flames at elevated pressures, which are needed for model validation. Temperature sensitivities were deduced for RDX and nitramine propellants, and ignition delays were deduced for RDX, HMX and RDX/CAB pseudo propellants. In situ observation of burning surfaces revealed the formation of complex, sooty like structures and intermittent flame attachment. A liquid strand burner was established and successfully demonstrated to have the capability of maintaining a steady liquid propellant (LP) burning surface at the tip of the feeding tube using nitromethane. The burning behavior of nitromethane was also characterized.
Book Synopsis Kinetics of Individual Combustion Reactions Over Wide Temperature Ranges, For Army Models by : Arthur Fontijn
Download or read book Kinetics of Individual Combustion Reactions Over Wide Temperature Ranges, For Army Models written by Arthur Fontijn and published by . This book was released on 1998 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt: The kinetics of reactions important for models of nitrate ester and nitramine propellant combustion, as well as a reaction of a potential halon replacement fire retardant, has been studied. The experiments, on isolated elementary reactions, have been made in a high-temperature reactor to yield rate coefficients k(T) in realistic temperature ranges. All k(T) given are in cu cm/ molecule/sec. The N + CO2 right arrow NO + CO reaction has given an upper limit value of 5x10(exp -16) at 1140 K and lower values at lower temperatures. This suggests that the reverse reaction is unimportant in dark zones. This is the first investigation of an N-atom reaction at high temperatures by a photolytic technique. As a check on the method, the N + O2 right arrow NO + O reaction was studied. It yielded k(400-1220 K) = 2.0x10(exp -18) T2.15 exp( -2557 K/T), which in the region of temperature overlap (
Book Synopsis Chemical Kinetics of Nitramine Propellants by : Melvyn Branch
Download or read book Chemical Kinetics of Nitramine Propellants written by Melvyn Branch and published by . This book was released on 1986 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper describes experimental measurements of the structure of a lean, premixed, laminar, flat flame of methane/nitrogen oxide/oxygen. The composition of stable species in the flame was measured by a cooled quartz sampling microprobe and gas chromatographic analysis. The composition of the intermediates CN, Ch, NH and NH2 was measured by laser-induced fluorescence spectroscopy using an excimer laser pumped tunable dye laser system. The flame has two luminous zones, one yellow and the other violet, separated by distinct, dark nonluminous zones. The concentration of NO2 has a maximum in the yellow zone while the concentrations of CN, NH, NH2 and NO are maximum in the violet region. The CH concentration profile has two peaks with one occuring in the yellow and one in the violet luminous zone. THe first peak is thought to be due to Ch4/02 reactions while the second peak is attributed to CH4/NO2 reactions. The oxidation of Ch4 is supported by the decomposition of NO2 to NO, although 02 is important in the initiation of the reaction process.
Book Synopsis Wide-Temperature Range Kinetics of Propellant Combustion Reactions by :
Download or read book Wide-Temperature Range Kinetics of Propellant Combustion Reactions written by and published by . This book was released on 2006 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt: The goal of this work is to provide accurate chemical kinetic information on individual reactions for use in Army propellant combustion models. A critical review was prepared, discussing the best data for a number of dark zone species reactions. The effect of the rate coefficients, and their temperature dependence, on the models is described. Experimental and theoretical studies of NH reactions have been made. It is shown that HNO can not be a product of its reactions with CO2 and H2O. If it were, nitrate ester combustion would not show dark zones, contrary to the observations. For the NH + H2 reaction k(833-1432 K) was measured to be 3.5 x 10 ( -11)exp( -7758 K/T) cm(3)molecule( -1)s( -1).
Book Synopsis Nitramine Propellant Crack Tip Ignition and Crack Propagation of a Burning Sample Under Rapid Pressurization by :
Download or read book Nitramine Propellant Crack Tip Ignition and Crack Propagation of a Burning Sample Under Rapid Pressurization written by and published by . This book was released on 1983 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two major tasks performed during the report period of investigation were: 8i) crack tip ignition phenomena under rapid pressurization and (ii) crack propagation in burning solid propellants. Ignition of nitramine composite propellants located at the tip of an inert crack was investigated both experimentally and theoretically. A theoretical model is proposed for the ignition of nitramine composite propellants. Specific features considered in the model include: a) detailed chemical kinetics information for the ignition of nitramine composite propellants, b) two-dimensional (axisymmetric) geometry for the composite propellant, and c) rapid pressurization of the gas phase simulating actual rocket motor ignition conditions. It is found that the time required for the onset of gas evolution of nitramine propellants decreases as the pressurization rate is increased. Under the same operating conditions, nitramine-based composite propellants are harder to ignite than AP-based propellants. Nitramine propellants with HMX fillers are slightly more difficult to ignite than RDX-based propellants due to higher thermal diffusivity and activation energy for decomposition.
Book Synopsis Gas Phase Combustion Chemistry of Nitramine Propellants by :
Download or read book Gas Phase Combustion Chemistry of Nitramine Propellants written by and published by . This book was released on 1988 with total page 29 pages. Available in PDF, EPUB and Kindle. Book excerpt: The details of the chemical processes which occur during propellant combustion are generally not known, yet, they directly affect such important propellant combustion characteristics as ignition and burn rate. Recently, a collaboration has been set up to study these details in a coordinated and comprehensive way. This study is concentrating on nitramine-based propellants since their ignition and burn rate properties are of great current interest and importance. This report presents initial results of a long-term study in which both theoretical and experimental efforts are being pursued. Major results in theory include the calculation of thermochemical properties of a number of nitramine decomposition products and combustion intermediates, as well as specifying pathways for the formation of the reactive species HCN, H2CO, NO2 and N2O. Also, quantum chemical models for the interaction of nitrogen-type oxidizers with H atoms have been developed. Keywords: Propellant combustion, Nitramines, Cyanogen flames, Nitrogen dioxide flames.
Book Synopsis Chemical Kinetic Data Base for Propellant Combustion by : Wing Tsang
Download or read book Chemical Kinetic Data Base for Propellant Combustion written by Wing Tsang and published by . This book was released on 1991 with total page 55 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Combustion in Liquid-propellant Rocket Motors by : I͡U︡khanaĭ Khaimovich Shaulov
Download or read book Combustion in Liquid-propellant Rocket Motors written by I͡U︡khanaĭ Khaimovich Shaulov and published by . This book was released on 1964 with total page 260 pages. Available in PDF, EPUB and Kindle. Book excerpt: Contents: elements of kinetics of chemical reactions; homogeneous and heterogenous combustion; kinetics of chemical reactions in flame; Carburetion; steady-state regime of burning; instability of combustion process; simulation of process of burning.
Book Synopsis Fundamentals of Solid Propellant Combustion by : K. K. Kuo
Download or read book Fundamentals of Solid Propellant Combustion written by K. K. Kuo and published by . This book was released on 1995 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Kinetic Deuterium Isotope Effects in the Combustion of Nitramine Propellants by : Paul Chappell Trulove
Download or read book Kinetic Deuterium Isotope Effects in the Combustion of Nitramine Propellants written by Paul Chappell Trulove and published by . This book was released on 1988 with total page 216 pages. Available in PDF, EPUB and Kindle. Book excerpt: The deuterium isotope effect was used to investigate the rate limiting process in the combustion of nitramine propellants. Model propellant formulations containing either octahydro-1,3,5,7-tetranitro-1,3,5,7-tetrazocine (HMX), hexahydro-1,3,5-trinitro-1,3,5-triazine (RDX), or their deuteriated analogues were pressed into pellets and burned under nitrogen pressure in a window bomb. The magnitudes of the observed deuterium isotope effects indicate that the HMX and RDX exert significant control over the burning process of the studied propellants. Furthermore, assuming a consistent mechanism between decomposition and combustion, the observed isotope effects suggest that a carbon-hydrogen bond rupture in HMX and RDX is the rate controlling process in the combustion of the model nitramine propellants. HMX, RDX, Combustion, Isotope effects, Mechanism, Rate limiting reactions, Propellants, Nitramines.
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 700 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Book Synopsis Chemical Kinetics of Nitrogen-Hydrogen-Fluorine Systems of Interest as Rocket Propellants by : Donald I. MacLean
Download or read book Chemical Kinetics of Nitrogen-Hydrogen-Fluorine Systems of Interest as Rocket Propellants written by Donald I. MacLean and published by . This book was released on 1972 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt: The principle objective of the program was the study of the chemical kinetics of elementary reactions important in the combustion of several gas phase systems containing nitrogen, hydrogen and fluorine. Combustion system were selected with a view to providing information essential either to advanced rocket propellant technology or chemical laser design. The report briefly summarizes research completed during the four and one half year period from 1 March 1968 to 30 September 1972.
