石英/双酚E型氰酸酯复合材料的制备与性能

采用实验方法研究双酚E型氰酸酯树脂的黏度和固化特性,揭示催化剂对双酚E型氰酸酯树脂固化特性的影响规律;采用树脂传递模塑和真空导入模塑工艺制备石英纤维/双酚E型氰酸酯复合材料,并考察其力学性能。结果表明,双酚E型氰酸酯树脂室温至90℃范围内的黏度小于300 m Pa·s,凝胶时间大于10 h,起始固化温度、固化温度和终止固化温度分别为186±5℃,235±5℃和286±5℃;固化特征温度随着催化剂含量的增加而降低,直至催化剂饱和,其饱和范围为0.02%~0.03%,可使双酚E型氰酸酯树脂体系的固化温度降低约60℃,从而避免爆聚,实现液相法成型其复合材料;真空导入模塑工艺制备的石英纤维/双酚E型氰酸酯复合材料的力学性能明显优于树脂传递模塑制备试样。     

复合推进剂中硝酸铵的改性研究

在分析硝酸铵的多晶现象和吸湿特性的基础上 ,探讨了硝酸铵的改性技术。采用热分析法研究了无机添加剂对硝酸铵晶型转变的影响 ,并用高分子表面处理剂对硝酸铵进行表面处理。结果表明 ,这种方法可以有效地改善硝酸铵的晶体结构和吸湿特性 ,为硝酸铵在复合推进剂中的应用提供了实验和理论依据。     

发射药的分解机理及其安定性研究

在研究发射药中硝酸酯的分解机理及其与发射药安定性关系的基础上,分析了热分解,水解和自动催化作用对发射药安定性的影响,以色谱法和粘度法等实验手段探索发射药安定性的变化规律,通过不同温度下发射药老化过程的动力学研究,提出了确定发射药安全使用寿命的可靠方法。     

硼酸酯添加剂的研究

介绍了硼酸酯合成的一般方法．所合成的硼酸酯经四球机试验显示出优良的抗磨性能．指出了硼酸酯添加剂在应用中存在的问题,并对硼酸酯添加剂的作用机理进行了浅析．     

聚合物材料与液氧相容性的研究

为研究聚合物材料与液氧的相容性,针对四种结构不同的环氧树脂与氰酸酯的共聚固化物,以液氧冲击敏感性试验作为其与液氧相容性的判定方法,通过热分析测试手段测定各固化物的恒温氧化热增重、热分解失重和闪点等热氧性能,并与其液氧冲击敏感性进行分析对照,证实环氧/氰酸酯类改性树脂与液氧不相容的程度与其常规热氧化反应的难易程度是一致的,提高其抗氧化性可以改善其与液氧的相容性。由此加深了对于聚合物与液氧相容性本质的认识,为进一步研究与液氧相容的聚合物材料指明了方向。作为常规分析手段的热分析,在聚合物与液氧相容性的科学表征中可发挥重要作用。     

复合固体推进剂颗粒填充模型及其统计特性分析

复合固体推进剂属于高填充比颗粒类复合材料,氧化剂和金属颗粒在基体中的随机分布使其在细观尺度具有非均质的特点。从细观尺度研究固体推进剂燃烧及力学性能时,必须考虑颗粒级配、空间分布和种类等因素的影响。采用分子动力学方法,以硝酸酯增塑聚醚高能复合固体推进剂为研究对象,将固体颗粒模型化为球形,生成其在基体内随机分布的颗粒填充模型。利用Monte-Carlo算法模拟计算颗粒填充模型细观结构的两点概率函数,并研究了颗粒填充体积分数、尺寸与级配等参数对其的影响规律。从统计意义上给出具有各态历经性、统计均匀性和各向同性特点的颗粒填充构型最小周期性代表体元尺寸,可有效减小后续研究的计算量,节约计算成本。所构建的推进剂细观几何构型及对最小周期性代表体元尺寸的计算为后续开展复合固体推进剂细观尺度燃烧、燃面处铝团聚及力学性能数值研究奠定了基础。     

Surface modification of ammonium nitrate by coating with surfactant materials to reduce hygroscopicity

Ammonium nitrate (AN) is promising oxidizer in green propellants. In this work, the physical coating method was improved to modify the surface of ammonium nitrate particles with different surfactant materials to reduce hygroscopicity. Cetylalcohol, stearic acid, stearyl alcohol, palmic acid, lauric acid, stearsmide, tetradecylamine, dodecylamine, and tetradecanol were used as coating surfactant agents. The hygroscopicity was tested for ammonium nitrate with and without coating. Fourier transform infrared (FTIR) and scanning electron microscopy (SEM) were used to characterize the surface of coated and uncoated ammonium nitrate. The mass ratio of coating layer and decline of absorption rate of ammonium nitrate coated by cetylalcohol were 1.00%, and 28.40%, respectively. The results indicate that coating with cetylalcohol surfactant have advantages over the other surfactants in term of low mass ratio of coating layer, and high decline of moisture absorption rate. Thus, cetylalcohol would be a promising coating surfactant material for ammonium nitrate. The idea and approach presented in this study have potential to made hydrophobic layer on the surface of particles to reduce hygroscopicity of AN, and also help the researcher to improving anti-hygroscopicity of ammonium salts.     

硝化棉对硝酸铵的包覆工艺研究

提出了用硝化棉对硝酸铵表面进行包覆的新方法,对包覆工艺条件进行了研究,得到了最佳包覆工艺条件,对包覆条件的产品质量和钝感特性进行了测试,结果表明,产品包覆均匀,不易受潮结块,撞击感度进一步下降。最后对影响试验工艺条件的因素进行了探讨。     

Formulation development and characterization of cellulose acetate nitrate based propellants for improved insensitive munitions properties

Cellulose acetate nitrate (CAN) was used as an insensitive energetic binder to improve the insensitive munitions (IM) properties of gun propellants to replace the M1 propellant used in 105 mm artillery charges. CAN contains the energetic nitro groups found in nitrocellulose (NC), but also acetyl functionalities, which lowered the polymer's sensitivity to heat and shock, and therefore improved its IM properties relative to NC. The formulation, development and small-scale characterization testing of several CAN-based propellants were done. The formulations, using insensitive energetic solid fillers and high-nitrogen modifiers in place of nitramine were completed. The small scale characterization testing, such as closed bomb testing, small scale sensitivity, thermal stability, and chemical compatibility were done. The mechanical response of the propellants under high-rate uni-axial compression at, hot, cold, and ambient temperatures were also completed. Critical diameter testing, hot fragment conductive ignition (HFCI) tests were done to evaluate the propellants' responses to thermal and shock stimuli. Utilizing the propellant chemical composition, theoretical predictions of erosivity were completed. All the small scale test results were utilized to down-select the promising CAN based formulations for large scale demonstration testing such as the ballistic performance and fragment impact testing in the 105 mm M67 artillery charge configurations. The test results completed in the small and large scale testing are discussed.     

Preparation of ammonium nitrate-based solid composite propellants supplemented with polyurethane/nitrocellulose blends binder and their thermal decomposition behavior

To improve the performance of solid composite propellants (SCPs) supplemented with ammonium nitrate (AN) as an oxidizer, the incorporation of energetic ingredients such as explosives, energetic binders or catalysts is a common effective approach. For this purpose, polyurethane (PU), a typical inert binder, was mixed with nitrocellulose (NC) as an energetic polymer. Numerous composite solid propellant compositions based on AN and NC-modified polyurethane binder with different NC ratios were prepared. The prepared formulations were characterized using Fourier transform infrared spectroscopy (FTIR), RAMAN spectroscopy, X-ray diffraction (XRD), electron densimetry, thermogravimetric (TG) analysis, and differential scanning calorimetry (DSC). A kinetic study was then performed using the iterative Kissinger-Akahira-Sunose (It-KAS), Flynn-Wall-Ozawa (It-FWO), and non-linear Vyazovkin integral with compensation effect (VYA/CE) methods. The theoretical performances, such as theoretical specific impulse, adiabatic flame temperature, and ideal exhaust gaseous species, were also determined using the NASA Lewis Code, Chemical Equilibrium with Application (CEA). Spectroscopic examinations revealed the existence of NC and full polymerization of PU in the prepared propellants. According to density tests, the density of the propellant increases as the nitrocellulose component increases. According to the thermal analysis and kinetics study, the increase in NC content catalyzed the thermal decomposition of the AN-based composite solid propellants. Based on the theoretical study, increasing the amount of NC in the propellant increased the specific impulse and, as a result, the overall performance.