高能氧化剂改性研究进展

高能氧化剂的改性是降低其机械感度的一种重要方法。对推进剂中的氧化剂进行改性,不仅可以降低单组分的机械感度,也能提高推进剂的力学性能和改善推进剂的工艺性能。综述了高能固体氧化剂CL-20、ADN、HNF、HMX、RDX的改性研究进展。     

高能推进剂钝感含能材料研究现状

钝感高能推进剂是当前固体推进剂的重要发展方向,降低高能固体推进剂感度主要技术途径是要采用低感度高能量的原材料,一方面是应用新型低感度含能原材料,另一方面是对现有含能原材料改性使之降低感度。高能推进剂所用钝感含能原材料主要分为3部分:能量高而感度低的氧化剂,低感度的含能黏合剂,低感度的含能增塑剂。在推进剂配方研制过程中通过选择应用这3类原材料来降低高能固体推进剂的感度,满足高能固体推进剂的钝感安全性能。论述了国内外上述3类钝感含能原材料的研究进展。     

含相稳定硝酸铵CMDB推进剂的机械感度和燃烧性能

通过测试撞击感度、摩擦感度和燃速,研究了含相稳定硝酸铵(PSAN)的改性双基(CMDB)推进剂的燃烧性能和机械感度。结果表明,PSAN可改善CMDB推进剂的机械感度;用PSAN作氧化剂,其推进剂的燃速低于RDX作氧化剂的燃速,压强指数高于后者的压强指数;1～5MPa压力范围内随PSAN在配方中含量的增加,推进剂的燃速降低,压强指数升高。     

炸药颗粒表面包覆研究进展

以包覆材料为主线,对国内外硝胺炸药（RDX、HMX等）颗粒表面包覆研究进行综述,对多种包覆方法、包覆材料及机理进行了总结,以及表面包覆对硝胺炸药的机械感度和推进剂、发射药的力学性能等的影响。并指出了今后研究工作中应注意的一些问题和研究重点。     

钝感推进剂研究进展及发展趋势

介绍了低易损炸药钝感机理和几种新型钝感推进剂的研究进展,总结了降低推进剂感度的技术途径及其发展趋势,认为对降低推进剂感度的含能黏合剂和真正钝感氧化剂的研制及其在推进剂中的应用将是今后研究的重点工作。     

下一代战术导弹固体推进剂研究进展

概括并评述了新型含能材料和以这些含能材料为主要组分的新型推进剂的研究近况,其中新型含能材料包括含能黏合剂、含能增塑剂和高能氧化剂(填料),新型推进剂包括CL-20推进剂、AND推进剂和HNF推进剂.认为以这些新型含能材料为基础的高能钝感低特征信号推进剂是下一代战术导弹固体推进剂的发展方向.附参考文献17篇.     

纳米Al/RDX混合物的安全性

为提高含纳米Al固体推进剂和PBX炸药的安全性,利用DSC、SEM、机械感度、火焰感度等测试方法,探讨了混合方法、混合比例、包覆改性等因素对纳米Al/RDX混合物安全性能的影响。结果表明,与筛分混合法相比,通过溶液法混合,纳米Al能均匀分散于RDX表面,使纳米Al/RDX的热分解活化能和热爆炸临界温度分别增加8.7%和4.5%,热安定性也提高;随着纳米Al含量的增加,纳米Al/RDX混合物的摩擦感度和撞击感度均减小,而溶液混合法所得样品的撞击感度明显高于筛混法;采用氟橡胶、炭黑B包覆纳米Al后混合物的撞击感度降低到包覆前的18.4%。     

钝感推进剂配方研究及发展趋势

从钝感黏合剂、钝感增塑剂、钝感高能填料以及新型复合材料等方面综述了国内外钝感固体推进剂配方及钝感方法进展。结果表明,HTPE黏合剂、BDNPF/A增塑剂、FOX-7高能填料以及HMX-TATB核-壳微粒等均可有效降低推进剂感度。今后钝感推进剂的重点研究方向主要为推进剂钝感机理、钝感推进剂能量与感度关系、钝感材料的匹配技术以及影响感度的综合因素等。     

硝胺炸药颗粒包覆研究及其进展

以对硝胺炸药颗粒包覆钝感的方法、材料以及包覆改性后的效果为线索。综述了国内外在此研究领域中的进展。介绍了表面改性对硝胺炸药颗粒的分散性、机械感度以及对发射药和推进剂的燃烧性能、力学性能的影响。并对今后的研究工作做出展望。     

硬脂酸包覆超细RDX及其撞击感度

为改善超细RDX的性能,采用硬脂酸(SA)为钝感添加剂,获得了以超细RDX为基的钝感混合炸药.通过测试接触角、计算表面能验证其包覆可行性,SA能够包覆UFRDX.用扫描电镜对包覆后的样品进行表征验证,并测试了SA包覆后的超细RDX的撞击感度.结果表明,其表面形貌得到明显改善,SA可降低其撞击感度,说明钝感剂SA的加入是降低炸药撞击感度的有效方法.     

GAP高能推进剂工艺性能调节

分析了聚叠氮缩水甘油醚(GAP)高能推进剂工艺性能不佳的原因,提出了调节其工艺性能的技术途径,研究了氧化剂粒度级配、浇注温度、混合工艺、不同相对分子质量黏合剂组合使用、提高力学性能添加剂、固化催化剂和工艺助剂等对GAP高能推进剂工艺性能的影响,通过合理配置混合工艺、组合使用工艺助剂TE和力学性能添加剂TD,可有效改善GAP高能推进剂的工艺性能。     

Characterization of the Structure in Highly Filled Composite Materials by Means of MRI

Modern solid propellants are highly filled composite materials. The essential ingredients of a composite propellant are a crosslinked binder, a polymer like polyurethane and an oxidizer. Furthermore, most propellant formulations contain a stabilizer, ballistic modifiers, high energy fuel additives, a wetting agent, plasticizers and other additives to adjust physical properties. The aging behavior of composite propellants is correlated with a change in mechanical properties. Background of the aging behavior of a composite propellant are micromechanical phenomena. Therefore, the understanding of micromechanical phenomena like matrix filler detachment, crosslinking and chain cleavage is the key to the understanding of aging behavior of composite propellants. In this paper it is shown how micromechanical phenomena can be observed by MRI (Magnetic Resonance Imaging).     

Development of a Surface Modification Method for a Sensitive Oxidizer with an Inorganic Substance

We investigated a surface modification method for potassium chlorate (PC) characterized by great combustibility and for potential usage as a gas generator with inorganic minerals such as talc etc. Samples modified by a wet method using a binder and those by a dry method using ordered mixture were conducted for their surface modification under a scanning transmission electron microscope (STEM) and by mapping according to element for element analysis with an energy dispersive spectrometer (EDS). Mapping by element suggested that the dry method enabled a relatively uniform, thin talc coating on the surface of the PC. The results of the mechanical energy sensitivity tests of the oxidizer composite containing the surface modified (desensitized) PC demonstrated formation of a low sensitivity product with a maximum friction sensitivity of over 13 times (BAM: 4.2 kgf→ over 55.2 kgf) and a maximum impact sensitivity determined by a drop hammer test of over 5 times (20 cm→ over 100 cm).     

Mechanical Properties of Smokeless Composite Rocket Propellants Based on Prilled Ammonium Dinitramide

Ammonium dinitramide (ADN) is a high performance solid oxidizer of interest for use in high impulse and smokeless composite rocket propellant formulations. While rocket propellants based on ADN may be both efficient, clean burning, and environmentally benign, ADN suffers from several notable disadvantages such as pronounced hygroscopicity, significant impact and friction sensitivity, moderate thermal instability, and numerous compatibility issues. Prilled ADN is now a commercially available and convenient product that addresses some of these disadvantages by lowering the specific surface area and thereby improving handling, processing, and stability. In this work, we report the preparation, friction and impact sensitivity and mechanical properties of several smokeless propellant formulations based on prilled ADN and isocyanate cured and plasticized glycidyl azide polymer (GAP) or polycaprolactone‐polyether. We found such propellants to have very poor mechanical properties in unmodified form and to display somewhat unreliable curing. However, by incorporation of octogen (HMX) and a neutral polymeric bonding agent (NPBA), the mechanical properties of such smokeless formulations were significantly improved. Impact and friction sensitivities of these propellants compare satisfactorily with conventional propellants based on ammonium perchlorate (AP) and inert binder systems.     

Effect of the physical state of the activators on the combustion of composite rocket propellants. I. The applied catalysts

The effects on the burning and thermal decomposition of composite rocket propellants, based on ammonium perchlorate and butyl rubber, of oxide coated catalysts applied to tge surface of the ammonium perchlorate crystals and introduced into the propellant in the form of a colloidal suspension are investigated. It is shown that the possibility of changing the burning rate by means of applying the catalyst on the oxidizer crystal surface is determined by the chemical nature, the content of the compounds deposited on the oxidizer surface, and by the structure of the coating formed on the ammonium perchlorate surface. Excluding the agglomeration of the catalytic additives using the developed methods, the variation in their dispersivity and the nature of localization in the propellant are the indicators of the propellant's performance efficiency within the region of small additive concentrations (up to 0.5%) in the propellant. Scientific Research Institute for Physicochemical Problems, Belorus State Univ., 220050 Minsk. Translated from Fizika Goreniya i Vzryva, Vol. 31, No. 6, pp. 82–88, November–December, 1995.     

Performance optimization of a standard-flow hybrid rocket engine

A method for performance optimization of a standard-flow hybrid rocket engine is considered. The method is based on inserting an additional amount of an oxidizer into a solid propellant with a prescribed distribution of the oxidizer mass fraction along the solid propellant charge. An analytical dependence is derived for the oxidizer fraction distribution that ensures uniform combustion and high efficiency of the solid propellant charge.     

BuNENA含能增塑剂的性能及应用

BuNENA(N–丁基硝氧乙基硝胺)是一种性能优良的新型含能增塑剂,在枪炮发射药和火箭推进剂应用中均受到研究者的广泛关注,并被进行系统研究。在发射药中,BuNENA具有塑化能力强、工艺性能好、感度低、能量高等优点,能进一步提高配方力学性能,其应用前景广阔。而在HTPE(端羟基聚环氧乙烷–四氢呋喃嵌段共聚醚)火箭推进剂中,BuNENA已被证明是一种对提高能量、降低感度和提高推进剂力学性能等具有明显作用的新型含能增塑剂,使用HTPE/BuNENA黏合剂体系的钝感固体推进剂的综合性能优于HTPB/AP(端羟基聚丁二烯/高氯酸铵)推进剂,并可满足钝感弹药(IM)要求,已在各种战术发动机中获得了实际应用。     

The properties of 1,3,3,5,7,7-hexanitro-1,5-diazacyclooctane (HCO) and its application in propellants

The properties of HCO and its application as a monopropellant were described. In comparison with HMX, it is also a high energetic explosive with high thermostability and can be used as an oxidizer in solid rocket propellants. Theoretical specific impulse of HCO-double base propellant systems were calculated and the burning rates and thermostability of propellant were experimentally determined. Propellants were prepared with a spray-casting process. As an oxidizer in solid rocket propellant, HCO shows better characteristics under certain aspects compared with HMX.