氧杂环丙烷类粘合剂合成研究进展

提高固体推进剂的能量是火炸药工作者永恒追求的目标之一。将含能粘合剂在固体推进剂中使用,能够有效提升固体推进剂的整体能量,已逐渐成为火炸药业内的研究热点。本文从聚叠氮缩水甘油醚、聚缩水甘油醚硝酸酯和硝基及硝胺基取代缩水甘油醚粘合剂出发,探讨了氧杂环丙烷类含能粘合剂的合成研究进展。     

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。     

理想的的固体推进剂粘合剂的分子结构

对粘合剂的分子结构和固体推进剂的力学以及流变性能之间的关系进行了研究.由发动机中药住的操作条件对推进剂力学性能的要求以及已有的加工技术对药浆流变性能的限制出发.反推得出固体推进剂粘合剂理想的分子结构.结构和加工要求是由三种类型的火箭发动机的应用要求决定的:航天转运、运载火箭和弹道导弹以及空对空战术导弹.考虑了可满足这些应用要求的三种一般的配方.除假想的全粘合剂推进剂外,还包括传统的复合和硝酸酯增塑的推进剂配方.对这三类中的各种配方按分子量、交联密度、溶解度参数、链的刚硬性、单体的摩擦系数、填充物的体积分数和增塑剂的体积分数确定了各种聚合物的分子特性.10个聚合物粘合剂系统的特性数据说明了它们的分子结构如何影响制得的推进剂的性能.     

固体推进剂中新型含能材料研究进展

提高能量是固体推进剂研发过程中一直追求的主要目标,配方中加入新型含能材料是提高推进剂能量水平最重要的技术途径。作者介绍了近年来国内外在含能粘合剂、含能氧化剂、含能增塑剂和新型燃料添加剂方面的研究进展,并提出了固体推进剂在含能材料方面的发展趋势。     

硝胺推进剂用键合剂的研究新动向

综述了硝胺固体推进剂中氧化剂-粘合剂间粘附的有关问题,讨论了脱湿现象及其后果,介绍了近几年国内外有关适用于硝胺推进剂体系的键合剂及其作用机理。     

IPN技术在推进剂黏合剂体系中的应用研究进展

系统介绍了互穿聚合物网络(IPN)技术在复合固体推进剂、硝酸酯增塑聚醚(NEPE)推进剂及改性双基推进剂黏合剂体系中的应用研究进展,特别综述了环氧乙烷-四氢呋喃共聚醚(PET)类、聚乙二醇(PEG)类和聚叠氮缩水甘油醚(GAP)类NEPE推进剂用黏合剂的IPN技术改性进展。最后总结了IPN技术在固体推进剂黏合剂体系中的应用,并对其未来的发展前景进行了展望。     

互穿聚合物网络技术在固体推进剂中的应用前景

分析了互穿聚合物网络(IPN)技术的特点,综述了IPN技术在固体推进剂粘合剂固化体系中提高固体推进剂力学性能、改善加工工艺性能和增强抗蠕变性能等方面的应用前景,并概述了IPN技术在固体推进剂衬层和包覆层中的应用。     

端官能团液体橡胶应用现状与开发进展

介绍了端官能团液体橡胶发展概况及其在固体火箭推进剂粘合剂,环氧树脂改性、密封和灌封,制备和浇注弹性体等领域的应用现状及开发前景。     

一种新型含能材料——叠氮有机化合物

介绍叠氮有机化合物作为含能粘合剂、含能增塑剂、高能氧化剂及其它含能添加剂在枪炮发射药、固体推进剂及高能炸药等含能材料中的应用。     

一种新型含能材料-叠氮有机化合物

介绍叠氮有机化合物作为含能粘合剂、含能增塑剂、高能氧化剂及其它含能添加剂在枪炮发射药、固体推进剂及高能炸药等含能材料中的应用。     

Synthesis,Characterization and Thermal Properties of Poly(glycidyl azide‐r‐3‐azidotetrahydrofuran) as Azido Binder for Solid Rocket Propellants

Azido polymers have been investigated as energetic binders in the area of solid rocket propellants. However, the low temperature mechanical properties of them are not comparable with the traditional propellant binders. In this work, a new kind of azido binder named poly (glycidyl azide‐r‐3‐azidotetrahydrofuran) (PGAAT) was successfully synthesized. The molecular structures of monomers and copolymers were characterized. The sensitivity and thermal properties of the azido binder were studied. The cationic copolymerization of 3‐methylsulfonyloxytetrahydrofuran with ternary cyclic ethers was confirmed. The PGAAT azido binder exhibited attractive features like low glass transition temperature (T_g, −60 °C) and high energy (1798 J/g). The results indicate that the polymer is a suitable candidate binder for the solid rocket propellants.     

含能黏合剂聚缩水甘油醚硝酸酯合成研究进展

聚缩水甘油醚硝酸酯(PGN)是一种高能、钝感、洁净的富氧黏合剂。从20世纪50年代开始,它就一直是国外重点研究的高能固体推进剂含能黏合剂之一,也是近年来应用于推进剂、火炸药和烟火剂中的最具应用前景的含能黏合剂。以时间为序,分3个阶段较为详细地介绍了国内外PGN合成研究进展,指出了各个时期PGN合成工艺的优缺点。     

Nonreinforcing filler–elastomer systems. I. Experiments based on model systems

Five methods were modified to test for interactions between binder and filler of composite solid propellants. Methods based on uncured binder or model compounds were rate of solution of binder from composite mixtures; centrifugal separation of binder from the filler; of composite mixtures; measurement of the contact angle between binder and filler; and adsorption of binder or model compounds by filler from solution. Stress–strain–birefringence was measured on cured binders containing small amounts of filler. In addition to the polymers used as binders and the model compounds, three physical forms of aluminum, and the additives tris [1-methylaziridinyl] phosphine oxide (MAPO) and a polysebacate of methyl-N-diethanolamine were included in the study. The filler was ammonium perchlorate in all experiments. The polysebacate was an effective adhesion improver in the polyurethane–ammonium perchlorate composite. MAPO was not as effective in the system polybutadiene–ammonium perchlorate. Fibrous forms of aluminum result in a weaker propellant then does powdered aluminum. Nonfunctionally terminated polymers were poorer in adhesion, contact angel, and adsorption tests compared with carboxyl- and hydroxyl-terminated types. The nonpolymeric model compounds yielded inconclusive data.     

B-GAP对复合固体推进剂能量性能影响理论研究

提高复合固体推进剂的能量性能的方法之一,是将普通的HTPB黏合剂替换成为含能黏合剂B-GAP.利用最小自由能法,对含能黏合剂B-GAP对复合固体推进剂的能量性能影响进行了理论研究,并计算出应用B-GAP的推进剂的燃烧室平衡温度、喷管出口温度、比冲等能量性能参数,将这些性能参数与丁羟推进剂进行比较,发现均有一定程度的提高...     

交联推进剂粘结剂体系的确定

在大量实验及资料的基础上,讨论了粘结剂体系（包括粘结剂、交联剂、交联催化剂及键合剂等）对交联推进剂性能的影响,提出了选择交联推进剂粘结剂体系的一些基本原则,并介绍了粘结剂体系的一些新进展,供配方设计及合成工作者参考。     

聚叠氮缩水甘油醚的合成与改性研究进展

聚叠氮缩水甘油醚(GAP)是国内外重点研究的含能粘合剂之一。该文综述了GAP的合成研究进展,重点介绍了高相对分子质量GAP、支化GAP和等规GAP的合成。针对GAP反应活性低的特点,介绍了GAP的多种端基改性方法。GAP的无规、嵌段共聚物改善了GAP粘合剂的性能,GAP与其他粘合剂的互穿及共混,为GAP在推进剂中的应用提供了广阔前景。引用文献37篇。     

Thermal Decomposition of RDX Composite Propellants

The thermal decomposition characteristics of RDX, binders, and RDX composite propellants were studied using thermal analytical techniques. Three kinds of binders were tested to elucidate the role of binder on the burning rate of the propellants. There were no apparent correlations between the thermal decomposition rates of binders and the burning rates of propellants, whereas there was a correlation between the decomposition temperature and the burning rate of the propellants. It is found that the major factor which controls the burning rate is the initial thermal-decomposition stage of the binders. Thus, the burning rate of nitramine composite propellants appeared to be largely dependent on the physical and chemical properties of binder.     

Thermal structural damage and thermal decomposition characterization of GAP propellants with nitrate ester plasticizers

GAP and nitrate ester compounds are introduced into the solid propellant formulation as energetic binders and energetic plasticizing agents, respectively, to further enhance the energy level of solid propellants. However, under abnormal thermal conditions, various components within GAP propellants, especially nitrate ester plasticizers, can collectively result in the generation of a large number of voids within the propellant due to factors such as thermal stress and slow component decomposition. This phenomenon can impact the safety of solid rocket engines, necessitating research into their thermal decomposition processes and thermal damage structures. In this study, the thermal decomposition characteristics and gas products of GAP propellants with different nitrate ester plasticizer formulations were investigated using DSC-TG and FT-IR. The damage structure of GAP propellants heated under unignited conditions was studied through Micro-CT, examining the influence of heating conditions and nitrate ester plasticizers on the thermal damage structure of GAP propellants. During heating, the thermal damage structure of GAP propellants was found to include voids generated within the GAP binder and cracks at the interface between the GAP binder and particles, with nitroglycerin as a plasticizer exacerbating the thermal damage of GAP propellants (about 2.2–2.9 times).     

Isocyanate‐Free and Dual Curing of Smokeless Composite Rocket Propellants

Traditional composite rocket propellants are cured by treatment of hydroxyl‐terminated prepolymers with polyfunctional aliphatic isocyanates. For development of smokeless composite propellants containing nitramines and/or ammonium dinitramide (ADN), energetic binder systems using glycidyl azide polymer (GAP) are of particular interest. Polyfunctional alkynes are potential isocyanate‐free curing agents for GAP through thermal azide‐alkyne cycloaddition and subsequent formation of triazole crosslinkages. Propargyl succinate or closely related aliphatic derivatives have previously been reported for such isocyanate‐free curing of GAP. Herein, we present the synthesis and use of a new aromatic alkyne curing agent, the crystalline solid bisphenol A bis(propargyl ether) (BABE), as isocyanate‐free curing agent in smokeless propellants based on GAP, using either octogen (HMX) and/or prilled ADN as energetic filler materials. Thermal and mechanical properties, impact and friction sensitivity and ballistic characteristics were evaluated for these alkyne cured propellants. Improved mechanical properties could be obtained by combining isocyanate and alkyne curing agents (dual curing), a combination that imparted better mechanical properties in the cured propellants than either curing system did individually. The addition of a neutral polymeric bonding agent (NPBA) for improvement of binder‐filler interactions was also investigated using tensile testing and dynamic mechanical analysis (DMA). It was verified that the presence of isocyanates is essential for the NPBA to improve the mechanical properties of the propellants, further strengthening the attractiveness of dual cure systems.