新型高能氧化剂及其在固体推进剂中的应用

综述了两种新型高能氧化剂多硝基氮杂环化合物ＨＣＯ和Ｋ－６的研究及其在固体推进剂中的应用，论述了多环氮杂硝基化合物和多硝基多环笼状化合物的特性及研究现状。     

洁净推进剂研究现状和展望

介绍了国外洁净推进剂的研究观状及清除洁净推进剂、中和洁净推进剂、无氯洁净推进剂的技术特点和性能水平,提出了我国开展洁挣推进剂研究的建议。     

硝酸铵基绿色洁净固体推进剂的研究进展

介绍了硝酸铵(AN)氧化剂的特点,综述了国内外AN的处理方法以及AN基固体推进剂研究的进展,总结了AN基固体推进剂的特点,认为AN的改性及提高燃烧性能将是研究AN基绿色洁净固体推进剂的重点,对我国开展AN基绿色洁净固体推进剂研究提出了几点建议.     

无机氧化剂二硝酰基胺铵在固体推进剂中的能量性能分析

为考察新型含能无机氧化剂二硝酰基胺铵(ADNA)对固体推进剂能量性能的贡献水平,采用编制的能量计算星程序5.0版,模拟计算了ADNA、ADN(二硝酰胺铵)及AP(高氯酸铵)对CMDB(复合改性双基)、HTPB(端羟基聚丁二烯)、NEPE(硝酸酯增塑聚醚)、GAP(聚叠氮缩水甘油醚)推进剂的能量贡献水平。结果表明:ADNA取代CMDB、HTPB、GAP、NEPE推进剂中的AP,都使体系标准理论比冲增加,羽流红外辐射性能降低;ADNA对推进剂的能量贡献要优于ADN,如果设计合适的HTPB、GAP配方体系,ADNA的能量贡献超越RDX。     

铝粉在固体推进剂中的应用

介绍普通铝粉及微米级铝粉在推进剂中的应用,介绍金属纳米铝粉的制备方法,综述了用于固体推进剂的纳米铝粉的突出效应,分析纳米铝粉在应用中亟待解决的问题。     

聚合物在固体推进剂中的应用进展

依固体推进剂的发展历程对聚合物在固体是剂中的应用作了一全面回顾，并分析了一些新型聚合物在固体推剂中的应用情况，展望了固体推进剂的发展趋势及聚合物在其中的发展应用前景。     

热塑性弹性体在固体推进剂中的应用

论述了热塑性弹性体用作固体推进剂粘结剂的重要性以及目前这一领域的研究状况，对热塑性弹性体在推进剂中应用所存在的问题和这一领域的主要研究方向进行了阐述。指出了热塑性弹性体是推进剂用粘结剂的一个重要发展方向。     

高能氧化剂硝仿肼及其推进剂研究的新进展

综述了欧美国家在研究高能氧化剂硝仿肼和以硝仿肼为基的固体推进剂等方面所取得的最新进展。介绍了硝仿肼的研制背景,并通过对硝仿肼物理化学特性数据的分析,证实了硝仿肼在固体推进剂中的实用价值。同时还介绍了以硝仿肼为氧化剂,ＧＡＰ为粘结剂,Ａｌ为燃料的固体推进剂配方的各种性能。     

固体推进剂用低特征信号氧化剂的研究进展

简要介绍了固体推进剂特征信号产生的原因及降低特征信号的几种途径。详细叙述ADN、CL–20、HNF和FOX–7等4种可降低特征信号的新型氧化剂的制备、性质和应用进展。指出了高性能固体推进剂的发展趋势。     

二聚酸二异氰酸酯在固体推进剂中的应用

简介了二聚酸二异氰酸酯(DDI)的主链结构及物性指标,详细叙述了DDI在丁羟(HTPB)推进剂药柱及绝热层、衬层、隔层中的应用情况,同时概括了其在聚醚推进剂和聚酯推进剂中的应用进展,认为绿色、无毒及来源于可再生原料的DDI是开发双推力推进剂、固体脉冲推进剂、富燃料推进剂及大型固体航天助推器推进剂的重要原材料,进行DDI的开发和应用对提高我国战术、战略武器的性能具有极大的促进作用。     

纳米材料在固体推进剂中的应用进展

从纳米含能材料、纳米金属粉、纳米催化剂及纳米碳材料4个方面综述了纳米材料在固体推进剂中的应用进展,归纳了各类纳米材料的特点及其在固体推进剂应用中存在的问题。指出了未来的研究方向,如纳米材料在固体推进剂中的分散技术、影响纳米材料微观形貌和粒度的因素、纳米材料在固体推进剂中的催化作用机理及利用纳米材料改善固体推进剂的力学性能等。     

Rheology of HTPB propellant. I. Effect of solid loading,oxidizer particle size,and aluminum content

Composite solid propellants based on hydroxyl-terminated polybutadiene (HTPB) have become the workhorse propellants in the present-day solid rocket motors. The other major ingredients of a composite propellant are the crystalline oxidizer and metallic fuel. As the solid loading of such propellants is as high as 86–90%, their rheological behavior is very complex. The propellant slurry needs to have reasonably low viscosity and a long pot life for better casting and, hence, for a defect-free rocket motor. The primary factors affecting the solid propellant viscosity are solid content, particle size, shape, and distribution. The present study concerns the variations of solid loading from 80 to 89% at constant aluminum cotent, variation of aluminium from 0 to 22% at constant solid loading, and the coarse-to-fine ratio of the oxidizer. The plots of yield stress, consistency index, pseudoplasticity index, and thixotropic index at different time intervals are drawn for all these parametric changes. Based on these rheological studies, the optimum ratio of oxidizer coarse-to-fine ratio, aluminum content, and level of solid loading have been determined.     

Induction period of a two-component aerosol of liquid oxidizer and propellant

The problem of self-ignition of a two-component aerosol consisting of uniformly mixed drops of an oxidizer and a propellant reacting in the gas phase is considered. The process of self-ignition of such an aerosol is divided into two stages: vaporization of aerosol components and subsequent chemical heating of the mixture. An approximate analytical formula is derived, for the period of self-ignition of a two-component aerosol. This formula takes into account the differences in thermophysical characteristics of aerosol liquids, mass concentrations, sizes of the drops of aerosol components, and the difference between the initial temperature of these drops and the initial temperature of the gas phase. The calculation results for the self-ignition period obtained using this analytical formula and the results of numerical solution of the problem in the zero-dimensional formulation coincide within 20% in a wide range of the governing parameters of the problem. Translated fromFizika Goreniya i Vzryva, Vol. 35, No. 6, pp. 15–21, November–December 1999.     

Effect of catalytic additives and aluminum particle size on the combustion of mixed compositions with a chlorine-free oxidizer

Experimental results on the stationary burning rate and solid content in the combustion products of mixed compositions with a chlorine-free oxidizer and an active fuel binder in the pressure range 0.025–6.0 MPa are presented. The effect of catalytic additives (silica and carbon black), the particle size of aluminum powder, and the method of preparing samples for combustion of the mixed compositions under consideration are analyzed.     

The migration of plasticizer in solid propellant grains

The migration of the plasticizer, dioctyl adipate (DOA) in the accelerated ageing of composite propellant has been studied. The method is based on the extraction of DOA with carbon tetrachloride and its estimation by gas chromatography. The concentration of DOA in the propellant at different distances from the insulation was determined after a definite ageing period and compared with the initial DOA concentration. The effect of (a) the ageing period, and (b) the ageing temperature on the degree of migration was examined. The present studies confirm the existence of plasticizer migration in the propellant adjacent to the insulation, during ageing.     

固体推进剂热安全性研究进展

综述了近年来固体推进剂热安全性的研究进展,认为固体推进剂发生热爆炸主要是由于推进剂生热速率大于散热速率导致热量累积。影响推进剂热安全性的因素主要由其组成、形状和尺寸等内因,以及贮存环境、老化时间等外部因素构成。固体推进剂热安全性研究多采用分析仪器与实验相结合的方法,借助计算机模拟仿真研究将是今后固体推进剂性能研究的重点。     

高能固体推进剂用粘合剂的研究进展

较为系统的从双基推进剂、复合固体推进剂、改性双基推进剂和NEPE推进剂等方面综述了其所用粘合剂的种类及其研究发展概况。介绍了当今新型含能粘合剂的类别和发展状况,并根据目前推进剂的发展要求,指出其粘合剂的发展趋势是含能化的热塑性弹性体。