共查询到19条相似文献,搜索用时 68 毫秒
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用高能氧化剂六硝基六氮杂异伍兹烷(CL-20)部分代替NEPE推进剂基础配方中的RDX,研究了CL-20含量、粒度大小对NEPE推进剂能量性能、燃烧性能、力学性能的影响规律。结果表明,在低铝含量NEPE推进剂中加入CL-20后,比冲可提高约54N.s/kg;加入CL-20后,NEPE推进剂在各压力点下的燃速明显比含RDX的NEPE推进剂燃速高,但压力指数差别不大;随着CL-20粒度的增加,燃速呈现先增后降的趋势,在105~125μm时达到最大值,燃速压力指数则表现为先降后增的趋势,105~125μm时最低,最低值为0.423;随CL-20粒径的变化,NEPE推进剂的力学性能有大幅度的变化,粒径为125~154μm时,其综合力学性能最佳。 相似文献
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通过用α-糠胺和乙二醛为原料合成了六糠基六氮杂异伍兹烷,对产物进行分离、提纯,目标产物的熔点为98.2~99.5℃。并通过正交实验法考察了温度、pH值、催化剂、时间等对产物收率的影响,确定了在温度为0~5℃、pH值为9~10、催化剂为高氯酸、时间为20h时产物的收率为42%。六糠基六氮杂异伍兹烷是一种新的具有六硝基六氮杂异伍兹烷(HNIW)构型的笼状前体,打破了过去只能用苄胺或取代苄胺来合成此前体的传统工艺,为两步法合成HNIW提供了有利的条件。即第一步HNIW笼状前体的合成,第二步前体的直接硝化合成HNIW。 相似文献
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针对浇铸中能无烟RDX-CMDB推进剂配方,进行了催化剂对燃烧性能影响的研究。对几种不同催化剂进行研究之后,选择了Ct-3催化剂。研究结果表明,在推进剂中加入适量的Ct-3,在15MPa压力下,推进剂的燃速由基础配方的19.60mm/s提高到26 ̄27mm/s,13 ̄20MPa下压力指数0.9以上降低到0.2左右。 相似文献
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纳米铝粉对硝胺炸药热分解催化性能的影响 总被引:2,自引:1,他引:2
采用直流电弧等离子体蒸发法制备了高纯度的纳米铝粉,并用比表面积分析仪和扫描电子显微镜(SEM)对样品进行了表征.将纳米铝粉与硝胺炸药HMX和RDX用研磨混合法制成混合粒子,用DSC对单质HMX和RDX炸药以及纳米铝粉/硝胺炸药混合物进行催化特性测试,并对样品的热分解动力学和热力学参数进行了计算和对比.结果表明,加入纳米铝粉后,HMX和RDX在不同升温速率(2、5、10、20 K/min)下的放热峰峰温降低,活化能分别降低15和16 kJ/mol,热力学参数都有明显变化.纳米铝粉对HMX和RDX有明显的热分解催化作用. 相似文献
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用DSC技术考察了7种含黑索今酮(Keto-RDX)火药的热分解特性,并对其中3种进行了密闭爆发器测试。将DSC数据对动力学方程进行拟合以求得动力学参数。从密闭爆发器测试结果转换得到了该3种火药的燃速-压力曲线,并对其进行了转折性分析。结果表明,向火药中加入Keto-RDX可提高火药燃速并降低其热分解表观活化能。含Keto-RDX的火药其燃速压力指数在低压区较在高压区为高。在火药中同时存在有Keto-RDX和RDX对火药热分解和燃烧的稳定性是不利的。仅由Keto-RDX与双基粘结剂组成的火药,其燃速压力指数较由RDX与双基粘结剂组成的火药为低。 相似文献
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《Propellants, Explosives, Pyrotechnics》2017,42(11):1252-1260
A nanocomposite microsphere consisting of solid paraffin, nano‐TiO2, nano‐BN, zeolitic imidazolate framework‐67 particles and polymethyl methacrylate was prepared and applied as a functional additive for high energy propellants (with about 23 wt % RDX) to reduce the barrel erosion and improve its combustion performance as well. High energy propellants modified with the nanocomposite were manufactured by a solvent extrusion technique. According to the scanning electron microscope and differential scanning calorimetry results, there exists a good compatibility between the nanocomposite and propellant matrix. The energy and combustion performance as well as erosion of the modified propellants were studied by a closed bomb test and an erosion tube device, respectively. Results showed that compared with the unmodified propellant, both the erosion and energy performance of modified high energy propellant gradually decreased with the increase of nanocomposites contents. When the content of nanocomposites was 5.1 %, the erosion mass of the modified propellant reduced to 37.0 % while the propellant force only decreased 5.7 %, indicating that the nanocomposite has enormous ability to improve gun erosion resistance while barely affect energy performance of propellant. Furthermore, the closed bomb burning curves of the samples showed that addition of nanocomposites to propellant matrix could prolong the combustion time, efficiently inhibit the initial generation rate of combustion gas, and further achieve the progressive burning of the propellants. 相似文献
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Wen Ao Yang Wang Heping Li Jianfei Xi Jianzhong Liu Junhu Zhou 《Propellants, Explosives, Pyrotechnics》2014,39(2):185-191
Only few data exist for experimental studies on ignition and combustion of boron particles with initial oxide thickness. The oxidation, ignition and combustion characteristics including the onset temperatures, weight gain, apparent activation energy, emission spectra during combustion, and ignition delay time of crystalline boron powders with different initial oxide thickness (x0) were studied by a laser ignition and thermogravimetric (TG) analyses. Simulations of the kinetics of oxide layer during boron ignition were conducted using a common model. The results indicated that the onset temperature was approximately 775 °C, independent of x0. The total weight gain decreased with increasing x0, whereas the weight gain at 775 °C did not change. The apparent activation energy was found to be insensitive to x0 and had a constant value of about 210 kJ mol−1. The intensity of the emission spectra gradually decreased while the ignition delay time increased with increasing x0. Numerical simulation showed that the removal rate of oxide layer enhanced with increasing x0. The experimental results revealed that the oxidation of boron powder was no diffusion‐controlled process at low temperatures. But the diffusion of oxygen could become important to the oxidation reaction at high temperatures 相似文献
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Gregory Young Jeremy J. Koeck Nathaniel T. Conlin Jordan L. Sell Grant A. Risha 《Propellants, Explosives, Pyrotechnics》2012,37(1):122-130
An experimental study on the effects of an applied external electric field on the combustion behavior of solid fuels and solid propellants has been conducted. In an opposed flow burning configuration, application of an electric field was shown to extinguish a paraffin fuel and gaseous oxygen flame over a broad range of operating conditions. When subjected to the electric field, burning paraffin fuel strands were found to extinguish at various axial locations relative to the exit of the oxidizer gas jet. Extinguishment location was found to be a function of field strength as well as electrode surface area, while changes in polarity did not significantly alter the results. In addition, the combustion behaviors of two composite solid rocket propellants were studied while subjected to an external electric field. Both propellants were based on HTPB/AP combinations, with one propellant containing aluminum and the other being non‐aluminized. Application of an electric field to the composite solid rocket propellant strands demonstrated decreases in propellant burning rate under all operating conditions for both propellants including changes in polarity. The flame structure of the aluminized propellant was examined closely as the luminosity, flame length, and flame width varied significantly with field strength and burning location of the strand relative to the electrodes. 相似文献