碳硼烷类燃速催化剂的研究进展

综述了国内外碳硼烷类燃速催化剂的研究情况,介绍了各种碳硼烷类催化剂的性能特点,指出碳硼烷类燃速催化剂是适用于高燃速和超高燃速推进剂配方的燃速催化剂,具有显著提高推进剂燃速的作用,对压强指数的影响依据配方组成的不同而有区别.     

多级燃速可控诱导压裂点火技术研究

以火工技术为主要手段的各种油气田增产技术已得到越来越广泛的应用,多级燃速可控诱导压裂技术提高了装药量和压裂药能量的利用率,延长了作用时间,大大加强了压裂效果,值得广泛推广。而研制合适的压裂药剂体系和点火控制系统是多级燃速可控燃爆诱导压裂的关键技术。本文通过一系列室内和地面模拟试验,确定了多级脉冲可控燃爆诱导复合药优化配方及组合匹配方案;并研制了一套全隔断式延时控制点火技术装置,解决了多脉冲高能气体压裂技术能量延时控制问题,延长对地层脉冲加载压裂的作用时间,进而达到延伸地层裂缝的目标,达到增产增注的目的,具有一定的现场指导作用。     

Theoretical Analysis of Plasma Enhancement of Propellant Burning Rate

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.     

苯乙烯环氧化反应金属配合物催化剂研究进展

介绍了国内外常用于苯乙烯环氧化反应的金属配合物催化剂,并对其研究概况、及对产率和转化率的影响作了简要介绍。     

烯烃聚合催化剂的研究

介绍了烯烃聚合催化剂的发展历程,分别讨论了Ziegler-Natta催化剂、茂金属催化剂和后过渡金属催化剂的研究情况,最后,提出了烯烃聚合催化剂的发展趋势。     

石油加氢脱硫催化剂载体的研究

介绍了目前加氢脱硫催化剂载体的种类和研究现状,包括氧化物载体、介孔分子筛载体、活性炭载体、酸碱载体等。分析了不同载体所具有的的优缺点,并展望了未来载体的研究方向。     

纳米氧化铅为燃烧催化剂的应用研究

运用红外光谱法研究纳米氧化铅对 HMX固相热分解的影响 ,通过静态靶线法燃速测试仪考察纳米氧化铅在推进剂中的实际应用效果。红外谱峰的变化表明 :氧化铅对 HMX的固相热分解直接起催化作用。通过纳米氧化铅在 NEPE推进剂中的实际应用效果表明 :纳米氧化铅可有效的降低 NEPE推进剂的燃速压力指数。     

Solid Propellant Burning Rate From Strand Burner Pressure Measurement

Strand burner pressure–time data are analyzed to determine if the propellant burning rate can be extracted. This approach is based on strand burner pressure–time history that is related to the temperature change due to exothermic reaction heating of chamber gases and gas addition to the chamber by propellant combustion products. In support of this method, chemical equilibrium calculations were made to project product composition, internal energy, and other needed properties. A mathematical model was formulated and solved numerically and the calculated burning rates were compared with the experimental wire‐break time results provided simultaneously and with the propellant manufacturer's results, when available. The comparisons reveal that the approach has merit and that more accurate pressure determination coupled with additional thermochemical information and strand burner gas temperature measurements has the potential to make this approach a viable technique and one that can be applied in conjunction with other burning rate measurements. The proposed method is similar to a well‐developed technique which is commonly applied to ballistic powders but with adjustments for the differences in geometry, pressure, and time of event.     

Correlations of Uncertainties of Composite Propellant Strand Burner Burning Rate Measurement for Quality Control

This study acquired, classified, and analyzed more than 3500 repeated‐measured steady state strand burner burning rate data from our quality control data bank as well as from open literature. The large size of consistent data from our resource were employed for the construction of a model that correlates burning rate standard deviations with average burning rates for both within‐batch lots and among‐batch lots. An increase in standard deviations with burning rates was observed for both correlations. Both correlations exhibit an R²‐statistic larger than 0.82 within burning rate range of 3.4–38.6 mm s⁻¹, and both correlations provide predictions in good agreements with some good quality published data. These two correlations may serve as feasible burning rate standard deviation tolerance reference when conducting composite propellants production quality control or burning rate data reproducibility checkup. Moreover, the confidence limits of parameters from the derived within‐batch correlation equation allow assessing the maximum pressure‐exponent uncertainties within selected burning rate range, thus provide insightful considerations to pressure‐exponent tolerance assignment for propellants under development or production.     

Evaluation of 4‐(Dimethylsilyl) Butyl Ferrocene Grafted HTPB as a Burning Rate Modifier in Composite Propellant Formulation using Bicurative System

High burning rate composite propellants are achieved by incorporation of fine particles of oxidizer, transition metal oxides, and liquid ballistic modifiers. However, they pose processing problems, inertness to the composition and migration related issues. To overcome such problems, an attempt was made to incorporate ferrocenyl grafted HTPB as a burning rate modifier by partly replacing HTPB from 10 % to 50 % using TDI/ IPDI bicurative system and to study their processability in terms of viscosity, mechanical, thermal, sensitivity, and ballistic properties. The data on viscosity reveal that there is a marginal enhancement in end of mix viscosity as percentage of ferrocenyl grafted HTPB increases. The mechanical data reveal that tensile strength and elastic modulus increases, whereas percentage elongation decreases compared to base composition. The results on thermal properties infer that, as the percentage of ferrocenyl grafted HTPB increases, onset decomposition temperature decreases. The impact and friction sensitivity data also envisage that sensitivity increases in comparison to base composition. The data on ballistic properties revealed that there is ca. 53 % increase in burning rate, while decrease in “n” value from 0.39 to 0.2 was obtained compared to base composition.     

Combustion Characteristics of a Novel Grain‐Binding High Burning Rate Propellant

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.     

Effect of Voids inside AP Particles on Burning Rate of AP/HTPB Composite Propellant

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.     

多基发射药燃烧性能的调节与优化

介绍了近来提出的多基发射药燃烧模型，利用其计算方法计算了多基发射药的化学组成对燃烧性能的影响；从化学结构和化学反应的层次分析了硝胺发射药燃速－压力曲线转折和某一压力范围内压力指数大于１的原因；从化学组成的角度出发提出了多基发射药燃烧性能优化设计的一些基本原则。     

合成乙酸正丁酯催化剂的研究进展

介绍了乙酸正丁酯的性能特点以及合成方法,讨论了合成乙酸正丁酯催化剂的研究进展情况,展望其发展方向。     

利用燃烧稳定剂调节燃速的研究

在不同燃烧稳定剂及常用稳定剂 Al2 O3不同粒度对燃烧速度影响研究的基础上 ,进一步探索了利用不同稳定剂以及 Al2 O3不同粒度复合来调节推进剂燃速的可能性     

Effects of Twin‐Screw Extrusion Processing on the Burning Rate of Composite Propellants

A new process for continuous manufacturing of composite propellants has been developed using Twin Screw Extrusion (TSE). The effects of TSE‐processing on the burning rates of an ammonium perchlorate (AP)‐based composite propellant have been characterized over a wide composition range (79 to 87 wt. % AP) and a wide range of screw speeds (45 to 85 RPM) using a quadratic model for an experimental Response Surface Analysis (RSA) based on the Kowalski, Cornell, and Vining (KCV) algorithm. Using Student‘s T‐test, it was determined that burning rates obtained from strand‐burning rate tests at 3.5 MPa, 7.0 MPa, and 10.5 MPa are affected only by the individual ingredients, the interaction between the coarse AP particles and the binder, and the screw speed. Measured burning rates were found to be 40% to 100% higher than Petite Ensemble Model (PEM) predictions, which was accounted for by modifying the PEM through a power law relationship with pressure that includes a rule‐of‐mixtures dependence of the exponent and coefficient on the weight fraction of coarse and fine AP particles. The resulting modified PEM reduced differences between the predictions and experimental data by 79% at 3.5 MPa, 83% at 7.0 MPa, and 78% at 10.5 MPa.     

降低固体推进剂燃速研究进展

综述了复合推进剂、硝酸酯增塑聚醚(NEPE)推进剂和改性双基推进剂在降低燃速方面的研究进展,并指出未来降低固体推进剂燃速研究的重点为向推进剂中引入含能降速剂及采用热分解温度较高且能量较高的新型含能材料。     

Burning Characteristics and Thermochemical Behavior of AP/HTPB Composite Propellant Using Coarse and Fine AP Particles

The burning rate of AP/HTPB composite propellant increases with increasing AP content and with decreasing AP size. In addition, the burning rate can be enhanced with the addition of Fe₂O₃. The burning characteristics and thermal decomposition behavior of AP/HTPB composite propellant using coarse and fine AP particles with and without Fe₂O₃ at various AP contents were investigated to obtain an exhaustive set of data. As the AP content decreased, the burning rate decreased and the propellants containing less than a certain AP content self‐quenched or did not ignite. The self‐quenched combustion began at both lower and higher pressures. The lower limit of AP content to burn the propellant with coarse AP was lower than that with fine AP. The lower limit of AP content to burn was decreased by the addition of Fe₂O₃. The thermal decomposition behavior of propellants prepared with 20–80 % AP was investigated. The decrease in the peak temperature of the exothermic decomposition suggested an increased burning rate. However, a quantitative relationship between the thermochemical behavior and the burning characteristics, such as the burning rate and the lower limit of AP content to burn, could not be determined.     

Iron Nanoparticle Additives as Burning Rate Enhancers in AP/HTPB Composite Propellants

Burning rate measurements were carried out for ammonium perchlorate/hydroxyl‐terminated polybutadiene (AP/HTPB) composite propellants with iron (Fe) nanoparticles as additives. Experiments were performed in a strand burner at pressures from 0.2 to 10 MPa for propellants containing approximately 80 % AP and Fe nanoparticles (60–80 nm) at concentration from 0 to 3 % by weight. It was found that the addition of 1 % Fe nanoparticles increased burning rate by factors of 1.2–1.6. Because Fe nanoparticles are oxidized on the surface and have high surface‐to‐volume ratio, they provide a large surface area of Fe₂O₃ for AP thermal decomposition catalysis at the burning propellant surface, while also providing added energy release due to the oxidation of nanoparticle sub‐shell Fe. The increase in burning rate due to Fe nanoparticle content is similar to the increase in burning rate caused by the addition of iron oxide (Fe₂O₃) particles observed in prior literature.     

固体推进剂燃速测试技术研究进展

综述了固体推进剂的静态燃速、动态燃速和特定环境下的燃烧测试技术的研究现状以及各种燃速测试方法的特点,分析认为固体推进剂燃速测试技术的总体发展规律是由静态燃速测试逐步发展到动态燃速测试,在动态燃速测试的基础上出现了旋转过载燃速测试技术和压强瞬变条件下的燃速测试技术。现有燃速测试技术还用于测试固体推进剂常用高能添加剂的燃烧性能。提出了固体推进剂燃烧性能测试技术的发展方向:高压(超高压)燃烧性能测试技术、超低压(真空)燃烧性能测试技术、低温微重力环境下的燃烧性能测试技术等。附参考文献55篇。