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Propellants
Selected AbstractsEffect of Voids inside AP Particles on Burning Rate of AP/HTPB Composite PropellantPROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 4 2008Makoto KohgaArticle first published online: 21 JUL 200 Abstract Bubble contamination in an ammonium perchlorate (AP)-based composite propellant has a positive effect on the burning rate. However, the quantitative effect of the bubble contamination on the burning rate has never been revealed. In order to clarify the relationship between the increase in the burning rate and the void fraction of the propellant, propellants were prepared with fine porous AP particles (PoAP) or fine hollow AP particles (HoAPs), and their burning rate characteristics were investigated. The voids inside AP particles have the effect of increasing the burning rate. The increase in the burning rate is enhanced linearly as the void fraction increases. The effect of the void fraction on the burning rate for a propellant containing PoAP is not identical with that for a propellant containing HoAP. It was found that the effect of the void fraction on the burning rate could be estimated by the void fraction when the bubble contamination is uniform in size and shape. [source] Combustion Characteristics of a Novel Grain-Binding High Burning Rate PropellantPROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 4 2008Xiaode Guo Abstract The novel grain-binding high burning rate propellant (NGHP) is prepared via a solventless extrusion process of binder and spherical propellant grains. Compared with the traditional grain-binding porous propellants, NGHP is compact and has no interior micropores. During the combustion of NGHP, there appear honeycomb-like burning layers, which increase the burning surface and the burning rate of the propellant. The combustion of NGHP is a limited convective combustion process and apt to achieve stable state. The larger the difference between the burning rate of the binder and that of the spherical granular propellants exists, the higher burning rate NGHP has. The smaller the mass ratio of the binder to the spherical granular propellants is, the higher the burning rate of NGHP is. It shows that the addition of 3 wt.-% composite catalyst (the mixture of lead/copper complex and copper/chrome oxides at a mass ratio of 1,:,1) into NGHP can enhance the burning rate from 48.78,mm,s,1 in the absence of catalyst to 56.66,mm,s,1 at P=9.81,MPa and decrease the pressure exponent from 0.686 to 0.576 in the pressure range from 9.81 to 19.62,MPa. [source] An Investigation of Composite Propellant Accelerated Ageing Mechanisms and KineticsPROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 3 2003Michael Abstract The ageing kinetics and mechanisms of a composite solid rocket propellant were investigated by monitoring unstressed propellant samples during prolonged storage at elevated temperatures. For samples confined under air during ageing, it was determined that oxidative cross-linking of the propellant binder was the main degradation mechanism over time. Plasticizer loss was a significant ageing mechanism only for those samples aged unconfined. In addition, there was an indication that ambient humidity had a significant but reversible effect on propellant mechanical properties. Arrhenius mathematical relationships were derived in order to ascertain the extent to which ageing was accelerated by increased propellant temperature. An activation energy for binder oxidation of between 71 and 74,kJ/mol was determined. [source] Spectral Acquisition and Calibration Techniques for the Measurement of Radiative Flux Incident upon PropellantPROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 1 2003Michael Abstract A technique for the absolute calibration of a time-resolved spectrographic system has been developed at QinetiQ, specifically designed to be relevant to spectral acquisition from within the interior of translucent gun-propellant samples. The technique has shown itself to be particularly useful in the realm of propellant ignition as it allows for the precise determination of the moment that propellant combustion processes begin, as well as measuring the incident radiative flux leading up to ignition. Scope exists to extend its use for high-pressure measurements of the incident radiative flux during both conventional propellant burn and high-powered electrothermal-chemical (ETC) discharges. This paper sets out to describe both the technique and some of the pitfalls encountered during the development of the technique. The use of this technique in some of the experimental work performed at QinetiQ, including the results of measurements that compare the incident radiative flux with propellant ignition during both ETC discharges and conventional gunpowder burn, have been published separately; references for this experimental work are given in this paper. [source] Thermal Behavior and Non-isothermal Decomposition Reaction Kinetics of NEPE Propellant with Ammonium DinitramideCHINESE JOURNAL OF CHEMISTRY, Issue 5 2010Weiqiang Pang Abstract Thermal decomposition behavior and non-isothermal decomposition reaction kinetics of nitrate ester plasticized polyether NEPE propellant containing ammonium dinitramide (ADN), which is one of the most important high energetic materials, were investigated by DSC, TG and DTG at 0.1 MPa. The results show that there are four exothermic peaks on DTG curves and four mass loss stages on TG curves at a heating rate of 2.5 K·min,1 under 0.1 MPa, and nitric ester evaporates and decomposes in the first stage, ADN decomposes in the second stage, nitrocellulose and cyclotrimethylenetrinitramine (RDX) decompose in the third stage, and ammonium perchlorate decomposes in the fourth stage. It was also found that the thermal decomposition processes of the NEPE propellant with ADN mainly have two mass loss stages with an increase in the heating rate, that is the result of the decomposition heats of the first two processes overlap each other and the mass content of ammonium perchlorate is very little which is not displayed in the fourth stage at the heating rate of 5, 10, and 20 K·min,1 probably. It was to be found that the exothermal peak temperatures increased with an increase in the heating rate. The reaction mechanism was random nucleation and then growth, and the process can be classified as chemical reaction. The kinetic equations of the main exothermal decomposition reaction can be expressed as: d,/dt=1012.77(3/2)(1,,)[,ln(1,,)]1/3 e,1.723×104/T. The critical temperatures of the thermal explosion (Tbe and Tbp) obtained from the onset temperature (Te) and the peak temperature (Tp) on the condition of ,,0 are 461.41 and 458.02 K, respectively. Activation entropy (,S,), activation enthalpy (,H,), and Gibbs free energy (,G,) of the decomposition reaction are ,7.02 J·mol,1·K,1, 126.19 kJ·mol,1, and 129.31 kJ·mol,1, respectively. [source] Maxwell Fluid Model for Generation of Stress,Strain Curves of Viscoelastic Solid Rocket PropellantsPROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 4 2010Himanshu Shekhar Abstract Solid rocket propellants are modeled as Maxwell Fluid with single spring and single dashpot in series. Complete stress,strain curve is generated for case-bonded composite propellant formulations by taking suitable values of spring constant and damping coefficient. Propellants from same lot are tested at different strain rate. It is observed that change in spring constant, representing elastic part is very small with strain rate but damping constant varies significantly with variation in strain rate. For a typical propellant formulation, when strain rate is varied from 0.00037 to 0.185 per second, spring constant (K) changed from 5.5 to 7.9,MPa, but damping coefficient (D) varied from 1400 to 4,MPas. For all strain rates, stress,strain curve is generated using developed Maxwell model and close matching with actual test curve is observed. This indicates validity of Maxwell fluid model for case-bonded solid propellant formulations. It is observed that with increases in strain rate, spring constant increases but damping coefficient decreases representing solid rocket propellant as a true viscoelastic material. It is also established that at higher strain rate, damping coefficient becomes negligible as compared to spring constant. It is also observed that variation of spring constant is logarithmic with strain rate and that of damping coefficient follows a power law. The correlation coefficients are introduced to ascertain spring constants and damping coefficients at any strain rate from that at a reference strain rate. Correlation for spring constant needs a coefficient "H," which is function of propellant formulation alone and not of test conditions and the equation developed is K2=(K1 - H)×{ln(d,2/dt)/ln(d,1/dt)}+H. Similarly for damping coefficient (D) also another constant "S" is introduced and prediction formula is given by D2=D1×{(d,2/dt)/(d,1/dt)}S. Evaluating constants "H" and "S" at different strain rates validate this mathematical formulation for different propellant formulations. Close matching of test and predicted stress,strain curve indicates propellant behavior as viscoelastic Maxwell Fluid. Uniqueness of approach is to predict complete stress,strain curves, which are not attempted by any other researchers. [source] Burning Behavior of Nitramine Gun Propellants under the Influence of Pressure OscillationsPROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 3 2010Gert Pauly Abstract By means of DNDA nitramine fractions in the formulation, it is hoped to produce gun propellants that have an almost temperature-independent burning behavior. The reason for this behavior is not clear yet. In the last years, it has become known that pressure oscillations may occur in the hole channels of gun propellant grains that may lead to a modification of the burning. To analyze the impact of such oscillations on the burning behavior of DNDA powders, tests with two different DNDA powders were performed in a closed vessel. In both cases, it could be demonstrated that the oscillations have a determining influence on the temperature behavior. [source] A Stochastic Pocket Model for Aluminum Agglomeration in Solid PropellantsPROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 2 2009Stany GallierArticle first published online: 19 MAR 200 Abstract A new model is derived to estimate the size and fraction of aluminum agglomerates at the surface of a burning propellant. The basic idea relies on well-known pocket models in which aluminum is supposed to aggregate and melt within pocket volumes imposed by largest oxidizer particles. The proposed model essentially relaxes simple assumptions of previous pocket models on propellant structure by accounting for an actual microstructure obtained by packing. The use of statistical tools from stochastic geometry enables to determine a statistical pocket size volume and hence agglomerate diameter and agglomeration fraction. Application to several AP/Al propellants gives encouraging results that are shown to be superior to former pocket models. [source] Separation and Determination of PETN and TNT by HPTLCPROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 1 2009Marzieh Chaloosi Abstract This article was published in Early View with DOI 10.1002/prep.200800012 , what is wrong. It has appeared with the correct DOI 10.1002/prep.200900012 , in Propellants, Explosives, Pyrotechnics 2009 (34) issue 1/2009 on pp 50-52. [source] An Investigation on Thermal Decomposition of DNTF-CMDB PropellantsPROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 6 2007Wei Zheng Abstract The thermal decomposition of DNTF-CMDB propellants was investigated by pressure differential scanning calorimetry (PDSC) and thermogravimetry (TG). The results show that there is only one decomposition peak on DSC curves, because the decomposition peak of DNTF cannot be separated from that of the NC/NG binder. The decomposition of DNTF can be obviously accelerated by the decomposition products of the NC/NG binder. The kinetic parameters of thermal decompositions for four DNTF-CMDB propellants at 6,MPa were obtained by the Kissinger method. It is found that the reaction rate decreases with increasing content of DNTF. [source] Investigation of the Decomposition Mechanism and Thermal Stability of Nitrocellulose/Nitroglycerine Based Propellants by Electron Spin ResonancePROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 2 2007Anton Chin Abstract Nitrocellulose based (NC) and nitroglycerin based (NG) propellants often have a fixed acid and water content during the manufacturing time. After manufacture, the quantity and ratio of acid/water will continue to vary depending upon the conditions of storage and operation. The level of variation depends on many factors such as loading density, temperature, volume of ullage and sealing condition of the containing cartridge, just to name a few. As described in this paper and other literature, the degradation mechanisms and aging processes of NC/NG based propellants are extremely complicated. This paper describes the details of the application of Electron Spin Resonance (ESR) to study if the free-radical mechanism is involved in the decomposition of nitrocellulose and nitroglycerin. Due to the high free-radical intensity possessed by the propellant composition, we believe that a , complex intermediate may be formed between DPA and NG and/or NC. The formation of a , complex intermediate is not preferred because it may enhance the rate of decomposition of nitrate esters. [source] Studies on Energetic Compounds Part,27: Kinetics and Mechanism of Thermolysis of Bis(Ethylenediamine)Metal Nitrates and Their Role in the Burning Rate of Solid PropellantsPROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 5 2003Gurdip Singh Abstract Four bis(ethylenediamine)metal(II) nitrate (BEMN) complexes, i.e. [M(EDA)2](NO3)2, where M=Cu, Co, Ni and Zn, have been prepared and characterized. Thermolysis of these complexes induced by heat and drop-weight impact has been investigated by TG-DTG, DTA, explosion delay (DE), explosion temperature (TE) and impact sensitivity measurement. The kinetics of early thermolysis reaction prior to fast decomposition have been evaluated. Contracting area (CA, n=2) and contracting cube (CC, n=3) equations were found to give the best fits in isothermal TG data among all tested nine mechanism-based kinetic models. The values of activation energy (Ea), TE, DE and activation energy for explosion (E*) have been found to be quite lower for the copper complex as compared to cobalt, nickel and zinc complexes. A mechanism of thermolysis has also been proposed. All these complexes were found to be insensitive towards impact of 2,kg weight up to the height of 110,cm. These complexes were used as energetic burning rate modifiers in the combustion of hydroxy-terminated polybutadiene (HTPB)-ammonium perchlorate (AP) composite solid propellants. A two-fold increase in burning rate was observed with copper and cobalt complexes at low concentration (2% by wt.). The in situ freshly formed metal oxides with large number of active sites in their crystallites seem to be better additives for combustion of propellants. [source] Evidence for the Hypothesis of Ignition of Propellants by Metallic Vapour DepositionPROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 6 2002Michael This paper examines the experimental evidence to support the hypothesis of ignition of energetic material by the process of metallic vapour deposition. The hypothesis has been presented previously, and this is the continuation of the work. The hypothesis has been developed at QinetiQ to explain certain measurements of incident radiative flux during electrothermal-chemical (ETC) experimentation, which show no correlation with the ignition event. Indeed, measured levels of radiation have been so low that radiative energy transfer for ETC plasma ignition could be said to be negligible. Measurement of the thickness of a metal layer resulting from dropwise vapour condensation gives good correlation to the flux requirements for ignition. [source] Aerogel and Xerogel Catalysts Based on ,-Alumina Doped with Silicon for High Temperature ReactionsEUROPEAN JOURNAL OF INORGANIC CHEMISTRY, Issue 3 2005Aurelien Florin Popa Abstract Numerous materials (supports and catalysts) based on alumina have been prepared using the sol-gel process and carbon dioxide supercritical drying. In this work two types of solids, i.e. xerogels and aerogels, were systematically compared and a way of introducing platinum metal with a content of 5% percent by weight was examined. The structural data, the surface area, Pt dispersion and catalytic activity for the decomposition of the propellant were measured for the various samples. The (Al2O3)0.88(SiO2)0.12 samples prepared show very interesting porosity values, especially for the aerogel. For this reason, they were chosen as supports for the synthesis of 5 wt% platinum on alumina catalysts. The results presented in this work allowed us to obtain an overall view of the influence of the preparation mode on the properties of platinum on alumina supported catalysts. The dispersion of the metal phase is directly dependent on the specific surface of the support. A significant value for the surface area implies a large amount of centers for interaction with the metal precursor and, consequently, the appearance of more centres of simultaneous germination. Although aerogels obtained by carbon dioxide supercritical drying always show superior properties compared with xerogels, for catalytic decompositions the xerogels still remain superior. (© Wiley-VCH Verlag GmbH & Co. KGaA, 69451 Weinheim, Germany, 2005) [source] Study of crack growth in solid propellantsFATIGUE & FRACTURE OF ENGINEERING MATERIALS AND STRUCTURES, Issue 10 2001E. E. Gdoutos The stress and displacement fields in an edge-cracked sheet specimen made of a solid propellant and subjected to a uniform displacement along its upper and lower faces was studied. The solid propellant was simulated as a hyperelastic material with constitutive behaviour described by the Ogden strain energy potential. A non-linear finite deformation analysis was performed based on the finite element code ABAQUS. A detailed analysis of the stress field in the vicinity of the crack tip was undertaken. The deformed profiles of the crack faces near the crack tip were determined. The results of stress analysis were coupled with the strain energy density theory to predict the crack growth behaviour including crack initiation, stable crack growth and final termination for two specimens with different dimensions. Crack growth resistance curves representing the variation of crack growth increment versus applied displacement were drawn. [source] Determining degree of saturation after application of transiently supersaturated metered dose aerosols for topical delivery of corticosteroidsJOURNAL OF PHARMACEUTICAL SCIENCES, Issue 2 2009Stuart A. Jones Abstract A transiently supersaturated drug delivery system has the potential to enhance topical drug delivery via heightened thermodynamic activity. The aim of this work was to quantify the degree of saturation (DS) for transiently supersaturated formulations using three traditional and one novel in vitro assessment methods. Metered dose aerosols (MDA) were formulated containing saturated levels of beclomethasone dipropionate monohydrate (BDP) or betamethasone 17-valerate (BMV) within a pressurised canister, and included ethanol (EtOH), hydrofluoroalkane 134a propellant and poly(vinyl pyrrolidone). Attempts to determine the DS via the measurement of drug flux through synthetic membranes did not correlate and was shown to be dependent on the EtOH concentration. The inability of these methods to accurately assess the drug DS may be due to the transient nature of the formulation and the volatile solvents dehydrating the membrane. A mathematical equation that used the evaporation rate of the formulation was derived to determine the theoretical DS at various time points after MDA actuation. It was shown that the MDAs became supersaturated with a high DS, this enhanced drug release from the formulation and therefore these preparations have the potential to increase the amount of drug delivered into the skin. © 2008 Wiley-Liss, Inc. and the American Pharmacists Association J Pharm Sci 98:543,554, 2009 [source] Single-dose study to compare the pharmacokinetics of HFA flunisolide and CFC flunisolideJOURNAL OF PHARMACEUTICAL SCIENCES, Issue 2 2002Arno Nolting Abstract The hydrofluoroalkane (HFA) formulation of the inhaled corticosteroid flunisolide is a modification of the original chlorofluorocarbon (CFC) formulation. HFA flunisolide replaces CFC with an HFA propellant and uses a built-in spacer in its pressurized metered-dose inhaler. The average HFA flunisolide particle size is 1.2 ,m compared with 3.8 ,m for the CFC formulation. The smaller particle size improves lung targeting, allowing a reduction in the HFA flunisolide dose relative to CFC flunisolide while maintaining comparable efficacy. In a study of 12 healthy men, pharmacokinetic parameters were determined after single doses of 1000 ,g CFC flunisolide delivered without a spacer, 340 ,g HFA flunisolide delivered through a spacer, and 516 ,g HFA flunisolide delivered without a spacer. A standard noncompartmental analysis of the concentration data was performed and mean (±,S.D.) pharmacokinetic values were reported. Peak plasma concentrations (observed Cmax) were similar for the three treatments. Area under the curve up to the time corresponding to the last measurable concentration (AUC0,tlast) was similar for the CFC and HFA flunisolide, plus spacer groups (4.4,±,1.6 ng·h/mL and 5.0,±,4.2 ng·h/mL, respectively); however, AUC0,tlast for the HFA flunisolide without spacer group was comparatively lower than for the CFC group (3.5,±,1.6 ng·h/mL). Observed Cmax and AUC0,tlast for 6,-OH flunisolide, the first-pass metabolite of flunisolide and an indicator of oropharyngeal deposition, were significantly higher in the CFC flunisolide group than in either HFA flunisolide group. © 2002 Wiley-Liss, Inc. and the American Pharmaceutical Association J Pharm Sci 91:424,432, 2002 [source] Short-term growth and adrenal function in children with asthma treated with inhaled beclomethasone dipropionate hydroflouroalkane-134aPEDIATRIC ALLERGY AND IMMUNOLOGY, Issue 8 2006O. D. Wolthers Inhaled beclomethasone dipropionate (BDP) with the propellant hydrofluroroalkane-134a (HFA) has been designed to be equivalent in terms of safety to chlorofluorocarbon (CFC)-formulated metered dose inhalers (MDI). The aim was to assess whether BDP HFA MDI 100 ,g twice daily was equivalent to BDP CFC MDI 100 ,g twice daily in terms of effects on short-term lower leg growth rate (LLGR) and measures of hypothalamic,pituitary,adrenal (HPA) function. The study consisted of a randomized double-blind cross-over trial with three active, a run-in and two wash-out periods each consisting of 2 wk. The place of study was a secondary referral outpatient clinic. The subjects involved were 14 boys and 10 girls with asthma, aged 7,12 yr. They were all administered BDP HFA 100 ,g, BDP CFC 100 ,g and 200 ,g twice daily. The outcome measures included LLGR and 24-h urine-free cortisol (UFC) and total cortisol metabolites (TCM). Mean (SD) LLGR during run-in and BDP HFA 100 ,g, BDP CFC 100 ,g and 200 ,g twice daily periods were 0.43 (0.23), 0.09 (0.29), 0.10 (0.45) and 0.08 (0.27) mm/wk. The one-sided 97.5% confidence interval for the difference in LLGR between BDP HFA 100 ,g and BDP CFC 100 ,g was 0.24, thus, below the predefined criterion of 0.20 mm/week. Inter-period comparisons of active treatments showed no differences between means of LLGR, UFC or TCM. Though non-inferiority between BDP HFA and CFC 100 ,g twice daily in terms of effects on LLGR was not found, equivalence was suggested by comparisons of LLGR during run-in and active treatments and by HPA function measures. [source] Maxwell Fluid Model for Generation of Stress,Strain Curves of Viscoelastic Solid Rocket PropellantsPROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 4 2010Himanshu Shekhar Abstract Solid rocket propellants are modeled as Maxwell Fluid with single spring and single dashpot in series. Complete stress,strain curve is generated for case-bonded composite propellant formulations by taking suitable values of spring constant and damping coefficient. Propellants from same lot are tested at different strain rate. It is observed that change in spring constant, representing elastic part is very small with strain rate but damping constant varies significantly with variation in strain rate. For a typical propellant formulation, when strain rate is varied from 0.00037 to 0.185 per second, spring constant (K) changed from 5.5 to 7.9,MPa, but damping coefficient (D) varied from 1400 to 4,MPas. For all strain rates, stress,strain curve is generated using developed Maxwell model and close matching with actual test curve is observed. This indicates validity of Maxwell fluid model for case-bonded solid propellant formulations. It is observed that with increases in strain rate, spring constant increases but damping coefficient decreases representing solid rocket propellant as a true viscoelastic material. It is also established that at higher strain rate, damping coefficient becomes negligible as compared to spring constant. It is also observed that variation of spring constant is logarithmic with strain rate and that of damping coefficient follows a power law. The correlation coefficients are introduced to ascertain spring constants and damping coefficients at any strain rate from that at a reference strain rate. Correlation for spring constant needs a coefficient "H," which is function of propellant formulation alone and not of test conditions and the equation developed is K2=(K1 - H)×{ln(d,2/dt)/ln(d,1/dt)}+H. Similarly for damping coefficient (D) also another constant "S" is introduced and prediction formula is given by D2=D1×{(d,2/dt)/(d,1/dt)}S. Evaluating constants "H" and "S" at different strain rates validate this mathematical formulation for different propellant formulations. Close matching of test and predicted stress,strain curve indicates propellant behavior as viscoelastic Maxwell Fluid. Uniqueness of approach is to predict complete stress,strain curves, which are not attempted by any other researchers. [source] A Stochastic Pocket Model for Aluminum Agglomeration in Solid PropellantsPROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 2 2009Stany GallierArticle first published online: 19 MAR 200 Abstract A new model is derived to estimate the size and fraction of aluminum agglomerates at the surface of a burning propellant. The basic idea relies on well-known pocket models in which aluminum is supposed to aggregate and melt within pocket volumes imposed by largest oxidizer particles. The proposed model essentially relaxes simple assumptions of previous pocket models on propellant structure by accounting for an actual microstructure obtained by packing. The use of statistical tools from stochastic geometry enables to determine a statistical pocket size volume and hence agglomerate diameter and agglomeration fraction. Application to several AP/Al propellants gives encouraging results that are shown to be superior to former pocket models. [source] Effect of Voids inside AP Particles on Burning Rate of AP/HTPB Composite PropellantPROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 4 2008Makoto KohgaArticle first published online: 21 JUL 200 Abstract Bubble contamination in an ammonium perchlorate (AP)-based composite propellant has a positive effect on the burning rate. However, the quantitative effect of the bubble contamination on the burning rate has never been revealed. In order to clarify the relationship between the increase in the burning rate and the void fraction of the propellant, propellants were prepared with fine porous AP particles (PoAP) or fine hollow AP particles (HoAPs), and their burning rate characteristics were investigated. The voids inside AP particles have the effect of increasing the burning rate. The increase in the burning rate is enhanced linearly as the void fraction increases. The effect of the void fraction on the burning rate for a propellant containing PoAP is not identical with that for a propellant containing HoAP. It was found that the effect of the void fraction on the burning rate could be estimated by the void fraction when the bubble contamination is uniform in size and shape. [source] Combustion Characteristics of a Novel Grain-Binding High Burning Rate PropellantPROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 4 2008Xiaode Guo Abstract The novel grain-binding high burning rate propellant (NGHP) is prepared via a solventless extrusion process of binder and spherical propellant grains. Compared with the traditional grain-binding porous propellants, NGHP is compact and has no interior micropores. During the combustion of NGHP, there appear honeycomb-like burning layers, which increase the burning surface and the burning rate of the propellant. The combustion of NGHP is a limited convective combustion process and apt to achieve stable state. The larger the difference between the burning rate of the binder and that of the spherical granular propellants exists, the higher burning rate NGHP has. The smaller the mass ratio of the binder to the spherical granular propellants is, the higher the burning rate of NGHP is. It shows that the addition of 3 wt.-% composite catalyst (the mixture of lead/copper complex and copper/chrome oxides at a mass ratio of 1,:,1) into NGHP can enhance the burning rate from 48.78,mm,s,1 in the absence of catalyst to 56.66,mm,s,1 at P=9.81,MPa and decrease the pressure exponent from 0.686 to 0.576 in the pressure range from 9.81 to 19.62,MPa. [source] Theoretical Analysis of Plasma Enhancement of Propellant Burning RatePROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 6 2007Roger Alimi Abstract A theoretical model of the combustion of a nitramine solid propellant in the presence of a plasma jet is proposed. Unlike standard double-base compositions, nitramine propellants exhibit experimental evidence that plasma induces a burning rate enhancement. The model is based on heat transfer considerations and proposes a closed-form solution of the enhancement of the propellant burning rate as a function of the thermophysical parameters of the system. The model provides a good qualitative agreement with experimental results. [source] An Investigation of Composite Propellant Accelerated Ageing Mechanisms and KineticsPROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 3 2003Michael Abstract The ageing kinetics and mechanisms of a composite solid rocket propellant were investigated by monitoring unstressed propellant samples during prolonged storage at elevated temperatures. For samples confined under air during ageing, it was determined that oxidative cross-linking of the propellant binder was the main degradation mechanism over time. Plasticizer loss was a significant ageing mechanism only for those samples aged unconfined. In addition, there was an indication that ambient humidity had a significant but reversible effect on propellant mechanical properties. Arrhenius mathematical relationships were derived in order to ascertain the extent to which ageing was accelerated by increased propellant temperature. An activation energy for binder oxidation of between 71 and 74,kJ/mol was determined. [source] Novel Segmented Thermoplastic Polyurethanes Elastomers Based on Tetrahydrofuran Ethylene Oxide Copolyethers as High Energetic Propellant BindersPROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 1 2003Fu-Tai Chen Abstract Novel thermoplastic polyurethane (TPU) elastomers based on copolyether (tetrahydrofuran ethylene oxide) as soft segments, isophorone diisocyanate and 1,4-butanediol as hard segments were synthesized for the purpose of using as propellant binders. In order to increase the miscibility of thermoplastic polyurethane elastomers with nitrate ester, polyethylene glycol (PEG) is incorporated in the co-polyether (tetrahydrofuran ethylene oxide) as soft segment. When the molecular weight and content of polyethylene glycol are controlled to 4000 and 6% of soft segments, respectively, the properties of thermoplastic polyurethane elastomers are most perfect. If plasticizing ratio of nitrate ester to thermoplastic polyurethane elastomers exceeds 4 no crystallinities are determined at room temperature. The propellant samples were prepared by a conventional absorption-rolling extrusion process and the mechanical and combustion properties evaluated afterwards. The maximum impulse reaches up to 265,270 s which is a little bit higher than that of a HTPB propellant. The measured results reveal a promising TPE propellant candidate which shows good processing temperature (<393,K) and excellent mechanical properties. An attracting feature which can be pointed out is that the burning rate pressure exponent reaches as low as 0.36 without the addition of burning rate catalysts. This enables an easy control of propellant combustion. [source] Migration of Plasticizer between Bonded Propellant InterfacesPROPELLANTS, EXPLOSIVES, PYROTECHNICS, Issue 1 2003Levi Gottlieb Abstract Plasticizer migration across bonded propellant interfaces during cure has been shown to have a measurable effect on propellant properties compared to each propellant by itself. This shows that the curing period is significant to the migration phenomenon. The plasticizer migration has been shown to have a direct influence on tensile strength for short aging periods up to the point the plasticizer reaches equilibrium. The tensile data for short aging periods have been shown to follow an empirical equation connecting the physical characteristics of plasticizer migration with increasing propellant tensile strength. The diffusion coefficient has been evaluated on the basis of this relation from a plot of , versus t1/2 and was in good agreement with the diffusion coefficient from the plasticizer content data. [source] Thermal Behavior and Non-isothermal Decomposition Reaction Kinetics of NEPE Propellant with Ammonium DinitramideCHINESE JOURNAL OF CHEMISTRY, Issue 5 2010Weiqiang Pang Abstract Thermal decomposition behavior and non-isothermal decomposition reaction kinetics of nitrate ester plasticized polyether NEPE propellant containing ammonium dinitramide (ADN), which is one of the most important high energetic materials, were investigated by DSC, TG and DTG at 0.1 MPa. The results show that there are four exothermic peaks on DTG curves and four mass loss stages on TG curves at a heating rate of 2.5 K·min,1 under 0.1 MPa, and nitric ester evaporates and decomposes in the first stage, ADN decomposes in the second stage, nitrocellulose and cyclotrimethylenetrinitramine (RDX) decompose in the third stage, and ammonium perchlorate decomposes in the fourth stage. It was also found that the thermal decomposition processes of the NEPE propellant with ADN mainly have two mass loss stages with an increase in the heating rate, that is the result of the decomposition heats of the first two processes overlap each other and the mass content of ammonium perchlorate is very little which is not displayed in the fourth stage at the heating rate of 5, 10, and 20 K·min,1 probably. It was to be found that the exothermal peak temperatures increased with an increase in the heating rate. The reaction mechanism was random nucleation and then growth, and the process can be classified as chemical reaction. The kinetic equations of the main exothermal decomposition reaction can be expressed as: d,/dt=1012.77(3/2)(1,,)[,ln(1,,)]1/3 e,1.723×104/T. The critical temperatures of the thermal explosion (Tbe and Tbp) obtained from the onset temperature (Te) and the peak temperature (Tp) on the condition of ,,0 are 461.41 and 458.02 K, respectively. Activation entropy (,S,), activation enthalpy (,H,), and Gibbs free energy (,G,) of the decomposition reaction are ,7.02 J·mol,1·K,1, 126.19 kJ·mol,1, and 129.31 kJ·mol,1, respectively. [source] Assessing the fate and effects of nano aluminum oxide in the terrestrial earthworm, Eisenia fetidaENVIRONMENTAL TOXICOLOGY & CHEMISTRY, Issue 7 2010Jessica G. Coleman Abstract Nano-sized aluminum is currently being used by the military and commercial industries in many applications including coatings, thermites, and propellants. Due to the potential for wide dispersal in soil systems, we chose to investigate the fate and effects of nano-sized aluminum oxide (Al2O3), the oxidized form of nano aluminum, in a terrestrial organism. The toxicity and bioaccumulation potential of micron-sized (50,200,µm, nominal) and nano-sized (11,nm, nominal) Al2O3 was comparatively assessed through acute and subchronic bioassays using the terrestrial earthworm, Eisenia fetida. Subchronic (28-d) studies were performed exposing E. fetida to nano- and micron-sized Al2O3 -spiked soils to assess the effects of long-term exposure. No mortality occurred in subchronic exposures, although reproduction decreased at ,3,000,mg/kg nano-sized Al2O3 treatments, with higher aluminum body burdens observed at 100 and 300,mg/kg; no reproductive effects were observed in the micron-sized Al2O3 treatments. In addition to toxicity and bioaccumulation bioassays, an acute (48-h) behavioral bioassay was conducted utilizing a soil avoidance wheel in which E. fetida were given a choice of habitat between control, nano-, or micron-sized Al2O3 amended soils. In the soil avoidance bioassays, E. fetida exhibited avoidance behavior toward the highest concentrations of micron- and nano-sized Al2O3 (>5,000,mg/kg) relative to control soils. Results of the present study indicate that nano-sized Al2O3 may impact reproduction and behavior of E. fetida, although at high levels unlikely to be found in the environment. Environ. Toxicol. Chem. 2010;29:1575,1580. © 2010 SETAC [source] Study of crack growth in solid propellantsFATIGUE & FRACTURE OF ENGINEERING MATERIALS AND STRUCTURES, Issue 10 2001E. E. Gdoutos The stress and displacement fields in an edge-cracked sheet specimen made of a solid propellant and subjected to a uniform displacement along its upper and lower faces was studied. The solid propellant was simulated as a hyperelastic material with constitutive behaviour described by the Ogden strain energy potential. A non-linear finite deformation analysis was performed based on the finite element code ABAQUS. A detailed analysis of the stress field in the vicinity of the crack tip was undertaken. The deformed profiles of the crack faces near the crack tip were determined. The results of stress analysis were coupled with the strain energy density theory to predict the crack growth behaviour including crack initiation, stable crack growth and final termination for two specimens with different dimensions. Crack growth resistance curves representing the variation of crack growth increment versus applied displacement were drawn. [source] Cough after inhalation of corticosteroids delivered from spacer devices in children with asthmaFUNDAMENTAL & CLINICAL PHARMACOLOGY, Issue 5 2003Jean-Christophe Dubus Abstract Children using a spacer device rather than another device for delivering inhaled corticosteroids (ICS) has been identified as a risk factor for cough immediately after inhalation. The aim of this study was to point out the different factors influencing the occurrence of such lateral side-effects. We studied this local side-effect in 402 asthmatic children (55.6 ± 34.9 months; 65.6% boys) treated for at least 1 month with beclomethasone dipropionate (n = 331), budesonide (n = 47) or fluticasone propionate (n = 24) delivered from pressurized metered-dose inhalers and small (75.1%) or large volume (24.8%) spacer devices mainly used with face mask (90.7%). A total of 219 patients (54.5%), treated with either high doses of ICS or ICS and long-acting ,2-agonist, were considered as having severe asthma. Cough was reported after each inhalation of corticosteroids in 216 patients (53.7%). Among them, about 30% also complained of cough with ,2-agonists. Despite different propellants and dispersants, all corticosteroids induced cough similarly. Cough was not linked with asthma severity, but was significantly related to therapy duration and use of long-acting ,2-agonist. Type and volume of the spacer device, use of a face mask or mouthpiece were not influencing factors. Cough after inhalation of corticosteroids delivered from spacer devices is a frequent local side-effect in children with asthma. This side effect can greatly alter compliance. A practitioner must be sought at each visit. [source] | ||||||||||||||||