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。     

丁羟推进剂中燃速催化剂的研究进展

使用燃速催化剂是调节丁羟推进剂燃速的最佳途径之一。综述国内外丁羟推进剂用燃速催化剂的研究进展,分析了发展趋势,结合纳米燃速催化剂和复合燃速催化剂优点的纳米复合燃速催化剂有望成为燃速催化剂的一个发展方向。其中,解决纳米粒子之间的团聚及在推进剂中的均匀分散问题是纳米复合燃速催化剂应用的关键技术。简要介绍这方面的部分探索性研究工作,尝试为解决纳米复合燃速催化剂的团聚问题找到新途径。     

丁羟推进剂的高效燃速催化剂

研制了二茂铁类新型燃速催化剂RF、FBB和GFP ,以及碳硼烷类高燃速调节剂NHC ,它们都是高沸点的液态物质 ,是丁羟推进剂的增塑型高效燃速催化剂 ,具有良好的综合使用性能。在推进剂配方中分别添加它们后 ,燃速可在 10～ 10 0mm/s(6 .86～ 9.8MPa)调节。和叔丁基二茂铁 (TBF)相比较 ,挥发性大小次序为 :GFP 相似文献   

二茂铁—优良的燃料燃速催化剂

根据国内外有关资料，提出了人造液化气，炉用燃料柴油（煤油）车用汽油柴油节能消烟添加剂的配比，重点介绍二茂铁燃速催化剂。     

颗粒粘结高燃速固体推进剂燃速的数值拟合

应用推进剂燃烧特征化学基团方法预估了推进剂中小粒药的燃速和速燃粘结剂的燃速，将预估结果与实验结果之间相相似理论的方法建立了计算机数值模拟公式。     

用ACP提高固体推进剂的燃速

用快燃物ACP提高改性双基推进剂、AP／HTPB复合推进剂和N-15D推进剂的燃速,取得了非常显著的效果。在HMX和RDX改性双基推进剂配方中加入不同粒度不同含量的ACP,推进剂的燃速均能提高,压强指数基本无变化。在AP基复合推进剂配方中加入ACP,其燃速均有不同程度的提高,而且在7～15MPa的压强范围内,压强指数小于0．45。成功地进行Ф64mm发动机试验,并获得稳定的P-t曲线。N-15D推进剂配方的燃速较低,加入ACP后,燃速也有提高,压强指数稍有增大。结果表明,加入ACP后燃速提高效率分别是：HMX改性双基推进剂配方为40．62％,RDX改性双基推进剂配方为38．00％,复合推进剂配方为37．35％,N-15D推进剂配方为9．90％。     

一种复合固体推进剂燃速预示改进方法

提出了某高氯酸铵(AP)-端羟基聚丁二烯(HTPB)复合固体推进剂燃速预示的一种改进方法.对燃速与多级配AP的总重均直径(dw)的相关性进行了研究,利用回归法得出了燃速与多级配AP的dw的线性关系式.利用该线性关系式,对复合固体推进剂燃速进行了预示,并通过配方调试验证,确定了全尺寸发动机装药AP多级级配.结果 表明,该...     

超低燃速复合固体推进剂的研制

概要介绍特种超低燃速复合固体推进剂的应用前景和研制的主要技术途径。     

关于固体推进剂燃速温度系数的探讨

介绍固体推进剂燃速温度系数的表达方法,综述有关固体推进剂燃速温度系数的理论,探讨了影响固体推进剂燃速温度系数的主要因素并对今后研究课题提出建议。     

Mechanical and burning properties of highly loaded composite propellants

An improvement in the performance of solid rocket motors was achieved by increasing the oxidizer content of HTPB-based solid propellants. To minimize the adverse changes in the mechanical and rheological properties due to the increased amount of hard solid particles in the soft polymeric binder matrix, the optimum combination of the particle sizes and volume fractions of the bimodal ammonium perchlorate and the aluminum powder in the solid load was obtained from the results of testing a series of propellant samples prepared by using ammonium perchlorate in four different average particle sizes, 9.22, 31.4, 171, and 323 μm. The maximum packing density of solids in the binder matrix was determined by changing the sizes and the volume fractions of fine and coarse ammonium perchlorate at constant solid loading. The average size (10.4 μm) and concentration of aluminum powder used as metallic fuel were maintained constant for ballistic requirements. Optimum sizes and fine-to-coarse ratio of ammonium perchlorate particles were determined to be at mean diameters of 31.4 and 323 μm and fine-to-coarse ratio of 35/65. Solid content of the propellant was then increased from 75 to 85.6% by volume by using the predetermined optimum sizes and fine to coarse ratio of ammonium perchlorate. Mechanical properties of the propellant samples were measured by using an Instron tester with a crosshead speed of 50 mm/min at 25°C. The effect of oxidizer content and fine-to-coarse ratio of oxidizer on the burning rate of the propellant was also investigated by using a strand burner at various pressures. From experiments in which the size and the fine-to-coarse ratio of ammonium perchlorate were changed at constant solid loading, a minimum value of initial modulus was obtained for each fine-to-coarse ratio, indicating that the solids packing fraction is maximum at this ratio. The tensile strength and the burning rate increase, while the elongation at maximum stress decreases with increasing fine-to-coarse ratio of ammonium perchlorate. Experiments in which the total solid loading was increased at constant fine-to-coarse ratio of ammonium perchlorate show that the modulus, the tensile strength and the burning rate increase, while the elongation at maximum stress decreases with increasing solid loading. Propellants having solid loading of up to 82% exhibit acceptable mechanical properties and improved burning properties suitable for rocket applications. © 1998 John Wiley & Sons, Inc. J Appl Polym Sci 67:1457–1464, 1998     

Ammonium perchlorate-based composite solid propellant formulations with plateau burning rate trends

This paper presents burning rates as a function of pressure of several propellant formulations based on ammonium perchlorate (AP) and hydroxyl-terminated polybutadiene cured by isophorone diisocyanate, many of which exhibit significantly low (nearly zero or negative) values of the pressure exponent of the burning rate in distinct pressure ranges, termed as plateau burning rate trends. The propellants contain a bimodal distribution of AP particles with the size of the coarse and fine particles within narrow ranges whose mean values are widely separated. Two mean sizes of fine particles were considered for the propellant formulations in the present work, namely, 5 and 20 μm. These choices are based on the mid-pressure extinction behavior exhibited by the matrix of fine AP and binder contained in the propellants but when tested alone over a wide range of fine AP size and pressure. The propellants that include the fine AP/binder matrixes exhibiting a mid-pressure extinction, in turn, exhibit the plateau burning rate trends within the corresponding pressure ranges. A plateau is also observed at elevated pressures in the burning rates of some formulations, which is related to the diminishing relative importance of the near-surface leading-edge region of the oxidizer/fuel diffusion flame in the gas-phase combustion zone. The choice of the coarse AP size influences the exact pressure range within the mid-pressure extinction domain of the matrix where the propellant exhibits the plateau burning rate trends. __________ Translated from Fizika Goreniya i Vzryva, Vol. 43, No. 4, pp. 73–81, July–August, 2007.     

Review of multi-scale mechanical behavior research on composite solid propellants based on data-driven approach

Composite solid propellant is a kind of viscoelastic composite with high filling ratio and multi-scale composition characteristics, and its macroscopic mechanical properties strongly depend on the microstructure of the propellant materia. However, with the increasing complexity of composition, structure and properties of composite solid propellants, the traditional research paradigm based on experimental observation, theoretical modeling and numerical simulation has encountered new scientific challenges and technical bottlenecks in the mechanical behavior analysis, charge design and manufacturing of composite solid propellants. Among them, the problems such as insufficient experimental observation, lack of theoretical model, limited numerical analysis and difficult verification of results restrict the development of composite solid propellants in future-oriented engineering applications to a certain extent. The data-driven computational mechanics method can directly establish complex relationships between variables from high-dimensional and high-throughput data, which can capture trends that are difficult to be found by traditional mechanics research methods, and has inherent advantages in the analysis, prediction and optimization of complex systems. This paper mainly reviews and evaluates the research of neural network based modeling, model-free data-driven calculation and data-driven multi-scale calculation, which provides the correct direction for the subsequent research of multi-scale mechanical behavior of composite solid propellants based on data-driven.     

Properties of the surface layer and combustion behavior of metallized solid propellants

The properties of the surface layer of burning metallized solid propellants are analyzed on the basis of available experimental data. A general physical concept of processes in the surface layer is developed. The structure called a skeleton layer is shown to play a key role in combustion. The factors influencing the properties of the skeleton layer are determined, and the effect of these of properties on the properties of condensed combustion products and the propellant burning-rate law is studied. __________ Translated from Fizika Goreniya i Vzryva, Vol. 45, No. 4, pp. 156–165, July–August, 2009.     

脱除NOx复合催化剂的研究

研究了以莫来石质多孔陶瓷作载体、溶胶-凝胶法Al₂O₃ 和TiO₂涂层作为扩表剂和Cu作为活性组分的系列催化剂的制备及催化活性分析。试验以NH₃为还原剂催化还原NOx,在自制NOx催化还原装置上,系统地考察了制备方法、Cu活性组分负载量和焙烧条件等因素对催化剂活性的影响。利用光学显微照片和XRD等表征方法对催化剂的物相结构进行了研究。     

复合固体推进剂填料/基体脱湿研究进展

概述了复合固体推进剂脱湿的表征方法,分析了各表征方法的优缺点,以及各表征方法适合研究脱湿的范畴,提出了可能的改进方向.概述了各因素对脱湿的影响:内因包括黏合剂基体模量,固体大颗粒含量、粒度、形貌等;外因包括测试温度、拉伸速率、应变率、湿热老化、环境压强等.提出对应的减少各因素影响脱湿发生的方法.     

固体推进剂用粘合剂研究进展

介绍了固体推进剂用粘合剂的研究进展,着重介绍了丁羟类、叠氮类、HTPE、NEPE以及硝基和硝酸酯类粘合剂的合成、工艺以及性能研究情况,并对未来固体推进剂用粘合剂的发展进行了展望。     

Experimental investigation of agglomeration during combustion of aluminized solid propellants in an acceleration field

Agglomeration during combustion of solid rocket propellants in an acceleration field up to 60 was studied experimental. In the experiments, the acceleration direction and magnitude were varied. The amount, chemical composition, and particle size of the agglomerates and the structure of the surface layer were determined as functions of the acceleration magnitude and direction. The most significant feature of the effect of tensile accelerations is an increase in the agglomerate mass to a certain limiting value, and that of compressive accelerations is the formation of a layer of condensed products on the burning-propellant surface. The data obtained provide a deeper understanding of the general physical picture of agglomerate formation and aluminized-propellant combustion and highlight the range of engine operation problems under flight conditions due to the presence of condensed combustion products. __________ Translated from Fizika Goreniya i Vzryva, Vol. 45, No. 1, pp. 38–46, January–February, 2009.     

Mechanism and laws of combustion of composite solid propellants with a coolant

The model of combustion of a composition consisting of a quasi-homogeneous composite propellant (matrix) and coolant particles is considered. The model is based on the leading role of exothermal decomposition of the matrix and on the cooling effect of the second component by virtue of transverse heat transfer between the components in the condensed and gas phases. Formulas for combustion characteristics (temperature, burning rate, its sensitivity to pressure, and initial temperature) are derived and analyzed. The calculated dependences of these characteristics on pressure, particle size, concentration, and thermal effects of decomposition of the components show that transitional regimes with a stronger dependence of the burning rate on pressure than that of the initial propellant are reached in a certain range of parameters. An algorithm is proposed, and a parametric identification of the model on the basis of experimental data is performed. __________ Translated from Fizika Goreniya i Vzryva, Vol. 43, No. 6, pp. 51–60, November–December, 2007.