DB/AP系燃烧剂的设计与性能研究

设计了以双基(DB)推进剂、高氯酸铵(AP)为主要组分的燃烧剂,并加入金属可燃剂B、Mg、Al来调整燃烧剂的燃烧性能,采用全自动量热仪、数码摄像机、热电偶和TG-DSC测试了燃烧剂的燃烧热、燃速、火焰温度和热性能.结果表明,金属粉的加入可以提高燃烧剂的燃烧热、燃速和火焰温度,并可以改变其火焰结构;对于长距离、高沸点物质的引燃,3种金属粉中B粉的效果最佳,DB/AP/B的火焰温度可达1 070℃,火焰长度达25cm,其燃烧过程也更稳定,而DB/AP/Mg和DB/AP/Al在燃烧过程中产生大量的火星;AP和金属粉对DB推进剂的热分解没有影响.     

DB/AP系燃烧剂的设计与性能研究（英文）

设计了以双基(DB)推进剂、高氯酸铵(AP)为主要组分的燃烧剂,并加入金属可燃剂B、Mg、Al来调整燃烧剂的燃烧性能,采用全自动量热仪、数码摄像机、热电偶和TG-DSC测试了燃烧剂的燃烧热、燃速、火焰温度和热性能。结果表明,金属粉的加入可以提高燃烧剂的燃烧热、燃速和火焰温度,并可以改变其火焰结构;对于长距离、高沸点物质的引燃,3种金属粉中B粉的效果最佳,DB/AP/B的火焰温度可达1 070℃,火焰长度达25cm,其燃烧过程也更稳定,而DB/AP/Mg和DB/AP/Al在燃烧过程中产生大量的火星;AP和金属粉对DB推进剂的热分解没有影响。     

Fe2O3/CNTs纳米粒子的制备及其对高氯酸铵燃速的催化作用

采用液相沉淀法制备沉积于碳纳米管（CNTs）表面的Fe2O3复合纳米催化剂,用透射电子显微镜（TEM）和光电子能谱（XPS）对制备的Fe2O3／CNTs复合纳米催化剂进行表征,研究了Fe2O3／CNTs复合纳米催化剂对高氯酸铵（AP）燃烧的催化性能。结果表明,纳米级Fe2O3颗粒均匀包覆在CNTs表面,Fe2O3／CNTs复合纳米催化剂能明显降低AP的分解温度,提高AP单元推进剂的燃速;Fe2O3／CNTs复合纳米催化剂对AP的催化活性明显优于纳米Fe2O3、纳米Fe2O3和CNTs的简单混合催化剂。     

Bi2O3/CNTS复合物的制备及其对双基推进剂燃烧的催化作用

以多壁碳纳米管、硝酸铋为原料,通过液相化学沉积法制备出Bi2O3/CNTs复合物.采用透射电镜(TEM)和X射线粉末衍射(XRD)对产物的粒子形貌、粒径和物相结构进行了表征,并考察了Bi2O3/CNTs复合物对双基推进剂燃烧性能的影响.结果表明,产物中Bi2O3以球状粒子的形式均匀地负载在碳纳米管表面,平均粒径约为27nm.Bi2O3/CNTs复合物能明显改善推进剂的燃烧性能,使推进剂的燃速提高74.7％(4MPa),压强指数(16～22 MPa)从0.7 834降低至0.4 307.     

B/Fe_2O_3/NC复合物的制备及其对HTPB/AP推进剂性能的影响

为改善硼粉(B)的性能和纳米氧化铁(Fe_2O_3)在固体推进剂中的分散性,用静电喷雾法制备了B/Fe_2O_3/NC复合物,采用扫描电镜(SEM)表征了复合物的表面形貌,用TG-DSC分析了复合物的热性能及其对HTPB/AP推进剂热性能的影响,并用燃速测试和密闭爆发器实验研究了该复合物对HTPB/AP推进剂燃烧性能的影响。结果表明,所制备的B/Fe_2O_3/NC复合物均以团聚体的形式存在,复合物中B的活性提高,其氧化反应温度提前;团聚硼粉对HTPB/AP推进剂燃烧性能的改善效果明显优于原料硼粉;加入Fe_2O_3后,会进一步改善含硼推进剂的燃烧性能,而且随Fe_2O_3含量的增加,在密闭爆发器中HTPB/AP推进剂达到最高压力所需的时间逐渐减小。当Fe_2O_3的质量分数为8%时,推进剂在常压空气中的燃速最大,为不添加B/Fe_2O_3/NC复合物的HTPB/AP推进剂的2.77倍。B/Fe_2O_3/NC复合物对推进剂的热分解具有一定催化作用,且随Fe_2O_3含量的增加催化作用增强。     

不同纳米材料含量对RDX-CMDB推进剂燃烧性能的影响（英文）

为研究3种纳米材料含量对改性双基推进剂燃烧性能的影响,系统地测试了含纳米铜粉(n-Cu)、纳米镍粉(n-Ni)和碳纳米管(CNTs)的含RDX改性双基(RDX-CMDB)推进剂的燃速。在此基础上,通过分析火焰结构、熄火表面和热分解特性探究了n-Ni对RDX-CMDB改性双基推进剂燃烧性能的影响机理。结果表明,质量分数为0.6%的n-Ni使RDX-CMDB推进剂6～16MPa的压强指数由0.29降至0.11。质量分数为0.8%的CNTs使已经含有Pb-Cu-C三组元催化剂的RDX-CMDB推进剂10MPa的燃速从17.12mm/s提高到22.12mm/s。n-Ni使RDX-CMDB推进剂分解放热量增加42.7%,同时提高了推进剂的燃面温度,这可能是n-Ni提高RDX-CMDB推进剂燃速的原因之一。     

p(BAMO-AMMO)热塑性高能推进剂燃烧转爆轰试验研究

采用燃烧转爆轰(DDT)管法研究了p(BAMO-AMMO)热塑性推进剂主要固体组分RDX和AP含量、AP粒度及级配等对其燃烧转爆轰响应规律的影响。结果表明,在相同试验条件下,含质量分数65%AP的p(BAMOAMMO)推进剂发生了燃烧转爆轰响应,而含等量RDX的p(BAMO-AMMO)推进剂仅发生了燃烧反应。当RDX质量分数从65%增加到85%时,样品由燃烧反应变为燃烧转爆轰反应。含等量细粒度(d50=1.0μm)AP的推进剂发生燃烧转爆轰的倾向较含粗粒度AP(d50=105μm)的低。当粗、细AP以质量比为10∶3级配时,p(BAMOAMMO)推进剂未发生燃烧转爆轰反应。     

碳纳米管对高氯酸铵燃烧和热分解的催化作用

通过干混法、水混法和丙酮混法制备了高氯酸铵（AP）与碳纳米管（CNTs）的复合物,研究TCNTs对AP燃烧和热分解的催化作用。结果表明：随着CNTs添加量的增加,AP／CNTs复合物的燃速增大,压力指数降低,对于相同CNTs添加量的AP／CNTs复合物,CNTs对AP的催化作用依赖于不同的混合方法,按干混法、水混法和丙酮混法的次序,催化作用依次增强,AP／CNTs复合物的燃速依次增大,压力指数依次降低。     

石墨烯在含能材料中的应用研究进展

从石墨烯及其复合物催化剂、石墨烯添加剂和石墨烯及其复合含能材料等3个方面,介绍了近年来石墨烯在含能材料应用方面的最新研究进展。认为石墨烯及其复合催化剂对推进剂含能组分具有明显的催化作用;添加石墨烯后,推进剂燃烧及力学性能得到改善;氧化石墨烯及石墨烯构成的钝感剂可降低含能材料的机械感度;石墨烯及其复合物含能材料具有优异的性能,更大的能量释放率。提出了石墨烯在含能材料领域的发展方向和应用前景。附参考文献42篇。     

CL-20粒度对GAP/AP/Al高能推进剂燃烧性能的影响

为了研究CL-20粒度对含Al高能固体推进剂燃烧性能的影响,通过捏合浇铸工艺制备了含不同粒度CL-20(14μm、115μm)的GAP/AP/Al高能推进剂,采用靶线法测定了推进剂在不同压强下的燃速,并计算了压强指数;利用微型高温热电偶测温技术、燃烧火焰单幅照相技术研究了CL-20粒度对该推进剂燃烧性能影响的机理。结果表明,7～18MPa下含粗粒度(115μm)CL-20的GAP/AP/Al推进剂的燃速比含细粒度(14μm)CL-20的推进剂高7%～37%;2～10MPa下前者压强指数为0.52,后者为0.46;粗粒度CL-20较细粒度提前进行部分分解,分解产物除催化自身分解反应外,还促进了AP的分解,从而提高了相应推进剂凝聚相反应区的温度攀升速率,并使推进剂的燃速更高。     

Friction sensitivity mechanism of Ammonium Perchlorate Composite Propellants

Friction sensitivity of ammonium perchlorate (AP) composite propellants has been studied experimentally by means of thermal analysis and micro-thermocouple techniques. Several types of catalysts were mixed with AP in order to examine the effect of the reactivity on the sensitivity. The results of friction sensitivity test show that the samples are sensitized when the concentration of catalysis which are used for high burning rate propellants is increased. Metal contents within the catalysts tend to give some effects on the friction sensitivity. Based on the results of the temperature profile measurements in combustion waves, it is found that the friction sensitivity is correlated with the burning surface temperature of the propellants. The catalysts which accclerate the AP decomposition are responsible for the friction sensitivity but not for the fallhammer sensitivity.     

高氯酸铵的催化热分解

用热分析技术研究了不同压力下几种多元催化剂或含能催化剂对AP热分解的影响，所研究的三种催化剂对AP高温分争的影响与粒度无关；从催化分解动力学参数解释了常压或低压与高压下的催化分解有不同的机理，推进剂燃速压力指数与AP高，低压下催化分解速率的不同有关。     

AP粒度对复合推进剂低速撞击响应的影响研究

为了研究AP粒度对复合推进剂低速撞击响应的影响,采用自行研发的落锤式撞击感度装置对含AP的复合推进剂进行了撞击感度研究,对比了相同组成下含不同粒度AP药柱的撞击响应敏感性,分析了AP粒度对复合推进剂低速撞击响应的影响规律,研究了不同粒度AP反应机理。结果表明,微米级中大粒度AP的复合推进剂更加敏感;AP粒度低至亚微米级,对复合推进剂低速撞击响应更加钝感。     

On the Thermal Stability of Partially Decomposed Ammonium Perchlorate

The response of propellants and explosives to thermal stimuli is an important aspect of their behavior, especially for their safe storage and handling. In the case of ammonium perchlorate (AP), the principal oxidizer used in solid composite propellants, exposure to elevated temperatures causes various levels of decomposition and morphological changes. These changes occur in both neat AP particles and AP based propellants. The hazards associated with thermally damaged, or partially decomposed AP are investigated. It is found that AP is more thermally stable after partial low temperature decomposition. Also, it is found that the extent of decomposition of the AP particles is strongly influenced by prior thermal damage. This dependency is attributed to the exhaustion of nucleation sites on certain crystal planes. Specific surface area measurements of the thermally damaged particles show that the particles recrystallize before they can decompose to a further extent in low temperature decomposition. The behavior of partially decomposed AP in the presence of a propellant binder is also examined.     

碳纳米管/聚合物基导热复合材料研究进展

碳纳米管（CNTs）由于优异的轴向导热性能,是目前制备高热导率聚合物基复合材料的一类重要填料。本文综述了近年来CNTs增强聚合物复合材料的研究进展,探讨了CNTs/聚合物复合材料的导热机理以及CNTs用量、尺寸及结构、表面改性、混杂CNTs粒子和聚合物基体结构等因素对CNTs/聚合物复合材料热导率的影响。同CNTs/聚合物的电导率相比,热导率远低于预期值,归因于CNTs/树脂界面间的声子频率失配现象导致了声子在界面的散射及很高的界面接触热阻,从而降低了体系热导率。分析和总结了改善体系热导率的方法和措施,采用特殊工艺使CNTs在基体内形成特殊的隔离结构或者取向结构是CNTs/聚合物导热复合材料的未来研究及发展方向。     

Hydrogenated Hydroxy-Terminated Polyisoprene as a Fuel Binder for composite solid propellants

The synthesis and application of hydrogenated hydroxy-terminated polyisoprene (HHTPI) to a fuel binder of composite solid propellants were attempted. An HHTPI prepolymer was synthesized through the hydrogenation for the hydroxy-terminated polyisoprene (HTPI) in the presence of nickel and zirconium catalysts over kieselguhr in 2.0 MPa hydrogen and at 443 K – 453 K for 24h. A prepolymer of a number-averaged molecular weight 2500–3800, provided a viscosity level required for the use of a fuel binder from which solid propellant can be possibly made by means of direct casting method. Thermal stability and aging characteristics of HHTPI elastomer against environmental attacks are superior to those of HTPB. Some plasticizers and bonding agents can bring about the acceptable mechanical properties to the propellant grains mainly composed of HHTPI, ammonium perchlorate and aluminium powder. The linear burning rates of HHTPI-based propellants are at the same level with that of HTPB-based propellants. However, the composition that gives the maximum performance with HHTPI-based propellants, shifts to 1–2 wt% fuel-rich side from the most adequate fuel content 12 wt% in HTPB/AP/Al. The HHPTI propellants indicated the similar burning rate as HTPB-based propellants in the linear burning rates in spite of the comparatively poor ignitability. Nevertheless, the static tests of 100 mm dia. sounding rocket motors are successfully performed by an ignition operation at the pressurized condition. The ballistic performances are not inferior to those of the HTPB-based propellants.     

碳纳米管材料导热性能的实验研究

本文对碳纳米管与环氧树脂(Epoxy-EP)复合材料的导热性能进行了定量的研究,探索了CNTs/EP复合材料的制备方法,运用Hotdisk热常数分析仪研究了CNTs/EP复合材料的导热系数;利用CNTs/EP两相复合材料的导热理论模型得到了室温下单壁碳纳米管(Single-Wall Carbon Nanotubes-SWCNTs)的导热系数为3980 W/(m.K),双壁碳纳米管的导热系数(Double-Wall Carbon Nanotubes-DWCNTs)为3580 W/(m.K),以及多壁碳纳米管(Multi-Wall Carbon Nanotubes-MWCNTs)的导热系数为2860 W/(m.K)。     

Thermal and ablative properties of binary carbon nanotube and nanodiamond reinforced carbon fibre epoxy matrix composites

The thermal and ablative properties of carbon nanotube (CNT) and nanodiamond (ND) reinforced carbon fibre epoxy matrix composites were investigated by simulating shear forces and high temperatures using oxyacetylene torch apparatus. Three types of composite specimens—(i) carbon fibre epoxy matrix composite (CF/Epoxy), (ii) carbon fibre epoxy matrix composite containing 0.1 wt-% CNTs and 0.1 wt-% NDs, and (iii) carbon fibre epoxy matrix composite containing 0.2 wt-% CNTs and 0.2 wt-% NDs—were explored. The ablative response of composites was studied through pre- and post-burnt SEM analysis and further related with thermogravimetric analysis, weight loss profile and thermal conductivity measurements. The novel nanofiller composites showed marked improvement in their thermal and ablative properties. A 22% and 30% increase in thermal conductivity was observed for composites containing 0.1 wt-% CNTs/0.1 wt-% NDs and 0.2 wt-% CNTs/0.2 wt-% NDs respectively. These nanofillers also improved the thermal stability of thermosetting epoxy matrix, and an increase of 13% and 20% was recorded in the erosion rate of composites containing 0.1 wt-% CNTs/0.1 wt-% NDs and 0.2 wt-% CNTs/0.2 wt-% NDs respectively. This improvement is due to the increased char yield produced by the increase in the loading of nanofillers, i.e. CNTs and NDs. Insulation index and insulation to density performance have also been improved due to increased thermal conductivity and char yield.     

Improving the performance of carbon/graphite composites through the synergistic effect of electrostatic self-assembled carbon nanotubes and nano carbon black

Superior performance fillers are considered as an effective means to enhance the performance of carbon/graphite composites. However, poor interfacial properties and incomplete filler networks limit the performance enhancement of the composites. In this study, a new method was proposed to weaken this impact through the synergistic effect of the electrostatic self-assembly of nano carbon black (NCB) onto carbon nanotubes (CNTs). The results showed that the synergistic effect between NCB and the CNTs significantly improved the mechanical and electrical properties of the composites. NCB reduces the porosity of the composites and increases the interaction between the CNTs and matrix. The compressive strength of the composite was 143.2 Mpa, and the flexural strength was 46.3 MPa, which is 210% higher than that of the pristine carbon/graphite composites. Moreover, NCB and CNTs form a globally connected synergistic network in the carbon skeleton. Composites filled with CNTs/NCB exhibited the lowest resistivity and highest thermal conductivity, with a resistance that was 42% lower than that of pristine carbon/graphite composites at 44.8 μΩ m. All of these results suggest that the synergistic effect of CNTs/NCB show great potential to improve the performance of carbon/graphite composites.     

Nitramine Solid Rocket Propellants with Reduced Signature

Solid rocket propellants containing nitramine are considerably superior to doublebase propellants, both as regards their performance and mechanical properties. The pressure exponent of non-modified nitramine propellants is n ≥ 0.9. The possibility of changing the burning rate or, respectively, the pressure exponent has, however, only been realisable to a restricted extent up till now in propellants with an increased nitramine content. In the following propellant system containing nitramine, the effects of ammonium perchlorate on burning behaviour are studied:

• ammonium perchlorate (AP)
• hexogen (RDX)
• nitroglycerin (NG), or trimethylolethane trinitrate (TMETN)
• polyurethane binder (PU)

AP concentrations already as great as 10% produce considerable changes in the burning behaviour of the propellants described above. It is possible to reduce the pressure exponent by the addition of ammonium perchlorate from n ≥ 0.9 to n ≤ 0.65. The burning rates may also be influenced with AP concentrations ≤ 20% and by varying the AP particle size by the factor of 2. All the propellants prepared were easily castable and showed exceptionally good viscoelastic properties (strain at break ε_R > 200%) in the temperature range between −40 °C to + 50 °C. The thermal chemical stability is not influenced negatively in any way by the combination of nitric acid esters and ammonium perchlorate.