Cu–Co–O nano-catalysts as a burn rate modifier for composite solid propellants

Nano-catalysts containing copper–cobalt oxides(Cu–Co–O) have been synthesized by the citric acid(CA) complexing method. Copper(II) nitrate and Cobalt(II) nitrate were employed in different molar ratios as the starting reactants to prepare three types of nano-catalysts. Well crystalline nano-catalysts were produced after a period of 3 hours by the calcination of CA–Cu–Co–O precursors at 550 °C. The phase morphologies and crystal composition of synthesized nano-catalysts were examined using Scanning Electron Microscope(SEM), Energy Dispersive Spectroscopy(EDS) and Fourier Transform Infrared Spectroscopy(FTIR) methods. The particle size of nano-catalysts was observed in the range of 90 nm–200 nm. The prepared nano-catalysts were used to formulate propellant samples of various compositions which showed high reactivity toward the combustion of HTPB/AP-based composite solid propellants. The catalytic effects on the decomposition of propellant samples were found to be significant at higher temperatures. The combustion characteristics of composite solid propellants were significantly improved by the incorporation of nano-catalysts. Out of the three catalysts studied in the present work, Cu Co-I was found to be the better catalyst in regard to thermal decomposition and burning nature of composite solid propellants. The improved performance of composite solid propellant can be attributed to the high crystallinity, low agglomeration and lowering the decomposition temperature of oxidizer by the addition of Cu Co-I nano-catalyst.

Comparison of burn rate and thermal decomposition of AP as oxidizer and PVC and HTPB as fuel binder based composite solid propellants

In the present investigation an effort has been made to understand the thermal decomposition and burn rate characteristics of AP as oxidizer and PVC and HTPB as fuel binder in composite solid propellant. The burning rate study has been carried out at ambient and different pressures of 2.068 Mpa, 4.760 Mpa,6.895 Mpa. The mechanism of thermal decomposition of each composition have also been determined by NETZSCH simultaneous thermal analyser, comprising differential scanning calorimeter(DSC) and thermo-gravimetric analyser(TGA). An effort has been made to study the burn rate and decomposition of fuel binder and oxidizer in presence of Fe_2O_3 and also their overall impact on combustion of propellant.

Humic Acid Effects on Reducing Corn Leaf Burn Caused by Foliar Spray of Urea-Ammonium Nitrate at Different Humic Acid/Urea-Ammonium Nitrate Ratios

Technologies for reducing corn leaf burn caused by foliar spray of urea-ammonium nitrate (UAN) during the early growing season are limited. A field experiment was carried out to evaluate the effects of humic acid on corn leaf burn caused by foliar spray of undiluted UAN solution on corn canopy at Jackson, TN in 2018. Thirteen treatments of the mixtures of UAN and humic acid were evaluated at V6 of corn with different UAN application rates and different UAN/humic acid ratios. Leaf burn during 1 2, 3, 4, 5, 6, 7, and 14 days after UAN foliar spray significantly differed between with or without humic acid addition. The addition of humic acid to UAN significantly reduced leaf burn at each UAN application rate (15, 25, and 35 gal/acre). The reduction of leaf burn was enhanced as the humic acid/UAN ratio went up from 10% to 30%. Leaf burn due to foliar application of UAN became severer with higher UAN rates. The linear regression of leaf burn 14 days after application with humic acid/UAN ratio was highly significant and negative. However, the linear regression of leaf burn 14 days after application with the UAN application rate was highly significant and positive. In conclusion, adding humic acid to foliar-applied UAN is beneficial for reducing corn leaf burn during the early growing season.

Effect of Burn-off Rate on the Microstructure and Mechanical Properties of the Friction Welded Joint

The effect of the burn off rate on the structure and mechanical properties in the friction welded joint of low alloy constructional steel 35CrMo is studied in this paper. The results show that the increase in the burn off rate and deceleration time of friction welding can improve the toughness of the weld. The mechanism of improving the toughness of the weld is the finer grain size and the lower hardness of the weld. In this paper the microstructure of the joint is also analysed . The fine granular structure in the area near the weld has been studied by TEM.The results indicate that the strengthening mechanism of the weld metal is the high density of dislocation, a number of second island phases and fine grain size. By means of measuring the carbon content of the area near the weld, the effect of the burn off rate on the highest heating temperature of friction welding has also been investigated.

Burning rate and other characteristics of strontium titanate （SrTiO3） supplemented AP/HTPB/Al composite propellants

In a quest of search for a new burning rate modifier for composite propellant, strontium titanate (SrTiO3), a perovskite oxide has been chosen for evaluation in a composite propellant formulation based on its other catalytic applications. Initially, SrTiO3 was characterized for particle size, morphology and material/ phase identification (using XRD). By varying SrTiO3 content in a standard composite propellant, different compositions were prepared and their performance and processing parameters like the end of mix (EOM) viscosity, mechanical properties, density, burning rate, pressure exponent (n-value), etc. were measured. The results reveal that 2% SrTiO3 causes more than 12% enhancement in propellant burning rate (at 70 ksc pressure) in comparison to the standard propellant composition. The pressure exponent also increases to 0.46, whereas the standard composition was having its value as 0.35.

Application of transient burning rate model of solid propellant in electrothermal-chemical launch simulation

A 30 mm electrothermal-chemical(ETC) gun experimental system is employed to research the burning rate characteristics of 4/7 high-nitrogen solid propellant. Enhanced gas generation rates(EGGR) of propellants during and after electrical discharges are verified in the experiments. A modified 0D internal ballistic model is established to simulate the ETC launch. According to the measured pressure and electrical parameters, a transient burning rate law including the influence of EGGR coefficient by electric power and pressure gradient(dp/dt) is added into the model. The EGGR coefficient of 4/7 high-nitrogen solid propellant is equal to 0.005 MW-1. Both simulated breech pressure and projectile muzzle velocity accord with the experimental results well. Compared with Woodley's modified burning rate law, the breech pressure curves acquired by the transient burning rate law are more consistent with test results. Based on the parameters calculated in the model, the relationship among propellant burning rate, pressure gradient(dp/dt) and electric power is analyzed. Depending on the transient burning rate law and experimental data, the burning of solid propellant under the condition of plasma is described more accurately.

Burning rate analysis of laser controlled 5-aminotetrazole propellant

As an innovative propulsion technique, laser augmented chemical propulsion(LACP) seems superior to the traditional ones. However, the corresponding combustion theories have still to be ascertained for LACP. Burning rate of 5-aminotetrazole(5-ATZ) propellant has been studied by testing pressed samples under different combustor pressures and laser powers. Based on micro computed tomography(Micro CT),an advanced thickness-over-time(TOT) method to characterize the regression of the produced nonplanar burning surface is established. Because of a shell structure covering the combustion surface,the burning rate of the implemented 5-ATZ propellant is not constant during laser ablation. Resorting to functional fitting, a new law of non-constant burning including the effect of the observed unique burning surface structures is proposed. Accordingly, applicable combustion conditions of 5-ATZ based propellants have been preliminarily speculated for future research activities.

Fuel Burning Rate Model for Stratified Charge Engine

A zero-dimensional single-zone double-curve model is presented to predict fuel burning rate in stratified charge engines, and it is integrated with GT-Power to predict the overall performance of the stratified charge engines. The model consists of two exponential functions for calculating the fuel burning rate in different charge zones. The model factors are determined by a non-linear curve fitting technique, based on the experimental data obtained from 30 cases in middle and low loads. The results show good agreement between the measured and calculated cylinder pressures, and the deviation between calculated and measured cylinder pressures is less than 5%. The zerodimensional single-zone double-curve model is successful in the combustion modeling for stratified charge engines.

CALCULATION OF BURNING RATE CHARACTERISTICS IN ACCELERATED FIELD FOR SOME ALUMINIZED SOLID PROPELLANTS

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Effects of Plasticizers,Antioxidants and Burning Rate Modifiers on Aging Performance of the HTPB/HMDI Composite Solid Propellant

The effects of plasticizers,antioxidants and burning rate modifiers on the aging performance of the composite solid propellant based on hydroxyl-terminated polybutadiene(HTPB)/hexamethylene diisocyanate(HMDI)were explored by apply-ing an accelerated aging program for 90 day at 70 ℃. The HTPB propellant matrix with the diisooctyl sebacate(DOS)as plasti-cizers and diisooctyl azelate(DOZ), antioxidants as N,N ′-Diphenyl-p-phenylenediamine(AO) and 2,2′-methylenebis(4-methyl-6-tert-butylphenol)(cyanox 2246)and burning rate modifiers as barium ferrite(BF),copper chromites(CC)and fer-ric oxide(FO)were varied. Results show that sample(S1)which based on DOS decreases the stress value and increases the strain value which considered to be an excellent start for aging program. Sample(S3)containing AO presents the higher resis-tance to oxidation showing the better performance that reflects on increasing the shelf life of the composite solid propellant mo-tor. Sample(S5)which based on BF enhances the ballistic performance among over the other tested two samples. The accelerat-ed aging program allowed us to estimate the motor in-service lifetime.

Effects of particle size and content of RDX on burning stability of RDXbased propellants

Particle size and content of RDX are the two main factors that affect the burning stability of RDX-based propellants. However, these effects and the corresponding mechanisms are still controversial. In this work, we investigated the physicochemical processes during burning and the corresponding mechanisms through the technologies of structure compactness analysis on the base of voidage measurement and theoretical interfacial area estimation, apparent burning rate measurement using closed vessel(CV)and extinguished burning surface characterization relying on interrupted closed vessel(ICV) and scanning electron microscope(SEM). The results indicate that the voidage increased with the increase of RDX content and particle size due to the increasing interfacial area and increasing interface gap size,respectively. The apparent burning rate increased with the increase of RDX particle size because of the decreasing RDX specific surface area on the burning surface, which could decrease the heat absorbing rates of the melting and evaporation processes of RDX in the condensed phase. Similarly, the apparent burning rate decreased with the increase of RDX content at pressures lower than around 55 MPa due to the increasing RDX specific surface area. Whereas, an opposite trend could be observed at pressures higher than around 55 MPa, which was attributed to the increasing heat feedback from the gas phase as the result of the increasing propellant energy. For propellants containing very coarse RDX particles, such as 97.8 and 199.4 μm average size, the apparent burning rate increased stably with a flat extinguished surface at pressures lower than around 30 MPa, while increased sharply above around 30 MPa with the extinguished surface becoming more and more rugged as the pressure increased. In addition, the turning degree of u-p curve increased with the increase of coarse RDX content and particle size, and could be reduced by improving the structure compactness.

Studies on composite solid propellant with tri-modal ammonium perchlorate containing an ultrafine fraction

Composite solid propellant is prepared using tri-modal Ammonium perchlorate(AP)containing coarse,fine and ultrafine fractions of AP with average particle size(APS)340,40 and 5 mm respectively,in various compositions and their rheological,mechanical and burn rate characteristics are evaluated.The optimum combination of AP coarse to fine to ultrafine weight fraction was obtained by testing of series of propellant samples by varying the AP fractions at fixed solid loading.The concentration of aluminium was maintained constant throughout the experiments for ballistics requirement.The propellant formulation prepared using AP with coarse to fine to ultrafine ratio of 67:24:9 has lowest viscosity for the propellant paste and highest tensile strength due to dense packing as supported by the literature.A minimum modulus value was also observed at 9 wt.%of ultrafine AP concentration indicates the maximum solids packing density at this ratio of AP fractions.The burn rate is evaluated at different pressures to obtain pressure exponent.Incorporation of ultrafine fraction of AP in propellant increased burn rate without adversely affecting the pressure exponent.Higher solid loading propellants are prepared by increased AP concentration from 67 to 71 wt.%using AP with coarse to fine to ultrafine ratio of67:24:9.Higher solid content up to 89 wt.%was achieved and hence increased solid motor performance.The unloading viscosity showed a trend with increased AP content and the propellant couldn't able to cast beyond 71 wt.%of AP.Mechanical properties were also studied and from the experiments noticed that%elongation decreased with increased AP content from 67 to 71 wt.%,whereas tensile strength and modulus increased.Burn rate increased with increased AP content and observed that pressure exponent also increased and it is high for the propellant containing with 71 wt.%of AP due to increased oxidiser to fuel ratio.Catalysed composite solid propellant is prepared by using burn rate modifiers Copper chromite and Iron oxide.Addition of Copper chromite and Iron oxide has enhanced the burn rate of tri-modal AP based composite solid propellant.The catalytic propensity of copper chromite is higher than that of iron oxide.The pressure exponent increased with the catalyst concentration and the values obtained are compatible for solid rocket motor applications.

NH_(3)/CH_(4)/CH_(3)OH多孔介质燃烧特性模拟研究

氨(NH_(3))是一种无碳燃料,有望作为热能发电的替代燃料降低碳排放。多孔介质燃烧是一种可提高燃烧速率和稳定性的燃烧技术,实验表明其用于氨与反应性更强的燃料进行混燃可以同时提高燃烧强度和燃烧稳定性,但缺乏相应的模型研究。该文基于多孔介质导热强度高的特性,其内部燃烧满足一维假设,建立了一维多孔介质燃烧模型,对NH_(3)分别与甲烷(CH_(4))、甲醇(CH_(3)OH)掺混时的燃烧特性进行模型计算。计算结果显示多孔介质对两种混合燃料的作用不同,对于CH_(4)/NH_(3)燃料,多孔介质可以明显提高燃烧速率并降低富燃状态的NH_(3)残留;对于CH_(3)OH/NH_(3)燃料,提高燃烧速率和降低NH_(3)残留的效果较差;对两种混合燃料,可燃气体预混后直接送入多孔介质燃烧都增加一定的NOx排放,增加效果相同,而分级燃烧可以显著降低NOx排放。

Synthesis of Cu-Chromite Catalyzer by Citrate Sol-Gel

It has been introduced several ways for rising fuel burning rate. Using catalyzers is a common way to rising fuel burning rate. Cu-Chromite catalyzer used in solid fuels, as burning rate catalyzer in thermal decomposition of Ammonium Perchlorate and results were satisfying. This catalyzer is produced by several methods such as: ceramic, coprecipitating, sol-gel, vacuum depositioning, but this paper explains producing catalyzer by Citrate sol-gel. Thermal analysis is used for studying process also SEM, XRD, TEM, FTIR tests used for determination of particle sizes.

RESEARCH ON RELATION BETWEEN MELTING POINT OF CEMENT CLINKER AND HEATING RATE

The relation between the melting point of Portland cement raw meal and its heating rate have been studied. The raw meal was burnt at different heating rate ranging from 10 similar to 900 degrees C/min Dy the following methods: (A) in electric resistance furnace; (B) in DTA-TG analyzer with infrared ray focused heating; (C) in high temperature microscope with electron stream heating. Based on thermal analysis theory and melt theory and the tests above, it is found that melting point T-m of cement raw meal decreases with the increased heating rate Phi during burning in the following relation: T-m=1280-0.107 empty set.

不同粒径黑火药点火过程中与纤维素壳体材料的热相互作用

为了研究点火装置中纤维素外壳对不同粒径黑火药固相反应放热特性、反应气相产物、点火燃烧特性等方面的影响,制备系列黑火药/纤维素复合物样品,并采用扫描电子显微镜表征其微观结构和形貌。通过同步热分析仪和傅里叶变换红外光谱仪联用,研究纤维素对黑火药热反应性能的影响。用氧弹量热仪测量各样品的爆热,利用综合燃烧诊断系统(高速相机和高速红外热像仪)获得黑火药及其纤维素复合物燃速与火焰温度分布。研究结果表明:纤维素会降低黑火药放热量,当纤维素含量为33.33%时,两种黑火药的总放热量分别降低了66.4%和58.5%;纤维素并未改变黑火药热解路径;黑火药的主要气相产物分别为H_(2)O、CO_(2)和NO_(2),与纤维素复合后除浓度变化外,气相产物种类保持不变;纤维素仅影响黑火药能量释放过程,但对不同粒径黑火药的能量释放影响的差别较小,与纤维素复合后能量释放变化仅相差3.1%。实验研究发现,小粒径黑火药及其纤维素复合物燃烧更剧烈,火焰面积更大、燃温更高;纤维素对黑火药的燃烧起消极作用,主要是降低黑火药的燃速和火焰辐射强度,火焰温度分别降低273.7℃和299.4℃;黑火药及其纤维素复合物的凝聚相产物形貌表明纤维素一定程度上促进了黑火药凝相产物团聚,即纤维素会降低其燃烧效率。

两种换药方式对降低经烧伤创面置股静脉管感染率的效果观察

目的 探究不同换药方式对经烧伤创面置股静脉管感染率的效果,进一步探究经烧伤创面置股静脉管的换药规范和标准。方法 选取2022年3月—2023年2月本院收治的烧伤创面置股静脉管患者60例为研究对象,随机将患者分成观察组(30例)和对照组(30例)。其中,观察组使用规范换药方式,对照组使用常规换药方式。对两组的感染率实施对比。结果 观察组总感染率明显小于对照组,两组数据具备统计学意义(P<0.05)。观察组总满意率明显大于对照组,两组数据有统计学意义(P<0.05)。结论 规范换药方式可降低导管感染发生率,有效提高经烧伤创面股静脉置管期间患者护理质量,提升期间的安全性,增强患者对标准用药的满意度,值得临床推广。

DNS Analysis on the Indirect Relationship between the Local Burning Velocity and the Flame Displacement Speed of Turbulent Premixed Flames

The local burning velocity and the flame displacement speed are the dominant properties in the mechanism of turbulent premixed combustion. The flame displacement speed and the local burning velocity have been investigated separately, because the flame displacement speed can be used for the discussion of flame-turbulence interactions and the local burning velocity can be used for the discussion of the inner structure of turbulent premixed flames. In this study, to establish the basis for the discussion on the effects of turbulence on the inner structure of turbulent premixed flames, the indirect relationship between the flame displacement speed and the local burning velocity was investigated by the flame stretch, the flame curvature, and the tangential strain rate using DNS database with different density ratios. It was found that for the local tangential strain rate and the local flame curvature, the local burning velocity and the flame displacement speed had the opposite correlations in each density ratio case. Therefore, it is considered that the local burning velocity and the flame displacement speed have a negative correlation.

超级铝热剂在固体推进剂中的应用研究进展

超级铝热剂具有高放热和高活性的特点,其反应速率和能量释放效率均显著高于传统铝热剂,应用于固体推进剂有望改善释能速率、效率、感度等指标,已成为固体推进剂的发展方向。总结了超级铝热剂的制备工艺、特点及其工业化应用潜力;论述了超级铝热剂在固体推进剂中的适用性;综述了超级铝热剂的微结构(燃料/氧化剂界面控制、核壳结构、多层膜结构)和组分(金属氧化物、氟材料、碳纳米材料)对固体推进剂燃烧性能和能量释放的影响。超级铝热剂的添加显著提高了热反应活性和放热量,增强了推进剂的点火及燃烧性能,同时存在工业生产成本高、工艺控制要求复杂、燃烧过程精密控制难度大等问题,展望了未来超级铝热剂在固体推进剂中应用的研究重点和发展方向。

降速剂及其作用位点对三组元推进剂燃烧性能的影响规律研究

针对两种典型季铵盐和金刚烷衍生物降速剂,研究了其作用位点对推进剂点火燃烧性能的影响。基于两种不同结构的Al@AP和AP@Al复合颗粒,将降速剂分布在不同作用位置:即AP颗粒内部和表面。利用扫描电子显微镜(SEM-EDS)和计算机断层扫描(CT)等技术对所制备复合颗粒微观形貌和结构进行表征,研究了降速剂对推进剂爆热、点火延迟和燃烧性能的影响。惰性降速剂的加入会使得推进剂爆热值降低,但Al@AP复合颗粒的高反应活性能部分抵消这一现象。与机械混合方式相比,当降速剂作用于AP表面时能明显延缓推进剂点火过程,其中金刚烷衍生物能使推进剂点火延迟时间增加至420 ms,比基础配方增加了192%。在基体中直接加入降速剂可以有效降低推进剂燃速,但其降压强指数效果有限。铝基复合颗粒和降速剂的共同作用能显著降低推进剂的高压燃速和压强指数:当作用位置在AP内时,两种降速剂使推进剂1~20 MPa内压强指数从基础配方的0.45分别降低至0.20和0.33,同时可使10~20 MPa压强指数分别减小了48%和49%。