HNIW单元推进剂燃烧性能研究

研究了一些添加剂对HNIW单元推进剂燃烧性能的影响,结果表明HNIW的燃烧受其分解过程的影响较大,在HNIW中加入其分解产物可显著降低其燃烧速度,所试的催化剂均对HNIW单元推进剂的燃烧性能有一定的催化作用。     

金属氧化物对HNIW单元推进剂燃烧的催化研究

对六硝基六氮杂异伍兹烷 (HNIW)的催化燃烧进行了初步的实验探讨 ,实验结果表明 ,HNIW单元推进剂的燃烧速度是 HMX单元推进剂燃烧速度的 2倍左右 ,HNIW单元推进剂的燃烧速度随着压力的增加而直线增加 ,其燃速压力指数为 0 .846 ,通过加入金属氧化物可使 HNIW单元推进剂的燃烧速度发生变化 ,但对其燃速压力指数影响不大     

含CL-20的NEPE固体推进剂的性能

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。     

含CL-20改性双基推进剂的燃烧性能

设计了两组不同含量CL-20或RDX改性双基(CMDB)推进剂配方,研究了CL-20或RDX含量对两组CMDB推进剂燃烧性能的影响。结果表明,在2～20MPa,CL-20改性双基推进剂的燃速高于RDX改性双基推进剂的。CL-20含量越高,CMDB推进剂压强指数变大。现有的铅、铜盐和炭黑催化剂可用于调节含CL-20改性双基推进剂的燃烧性能。     

四乙酰基二硝基六氮杂异伍兹烷的硝解研究

研究了ＴＡＤＮ在１００％ＨＮＯ３、Ｐ２Ｏ５／ＨＮＯ３、Ｎ２Ｏ５／ＨＮＯ３、Ｎ２Ｏ５／ＨＣＣｌ３、Ｎ２Ｏ５／ＣＨ３ＮＯ２、ＨＮＯ３／ＰＰＡ以及ＨＮＯ３／ＨＣｌＯ４等７种硝化剂中的硝解,结果表明这７种硝化剂均不适合用来硝解四乙酰基二硝基六氮杂异伍兹烷（ＴＡＤＮ）制备六硝基六氮杂异伍兹烷（ＨＮＩＷ）,同时发现在有硝酸的硝化剂硝解ＴＡＤＮ的过程中均出现了水溶性中间体。     

六糠基六氮杂异伍兹烷的合成及其工艺的研究

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。     

六硝基六氮杂异伍兹烷的热性能研究

叙述了 CL - 2 0热分解反应动力学和热分析研究结果。根据 90～ 14 0℃下真空等温热分解实验数据及相应曲线 ,导出了在不同温度下分解 0 .1%所需时间的经验公式 ,求得 CL- 2 0表观活化能 Ea=187.6 k J/ mol,指前因子 A=6 .9× 10 2 3 ,测得 CL- 2 0相变温度16 3.7℃ ,分解热 2 95 7J/ g,5 s爆发点 2 82 .2℃ ,10 0 0 s临界温度为 2 2 4℃。     

六硝基六氮杂异伍兹烷四种晶型的晶体结构

测定了六硝基六氮杂异伍兹烷四种晶型（α、β、γ及ε）的单晶结构,报道了它们的晶体学参数,给出了它们的分子构型,讨论了它们的结构,并与ＨＭＸ作了比较。     

硝胺推进剂燃烧性能的改善

选用了一种新型复合含能燃烧催化剂——ＰＮＴＯ／β－Ｃｕ／ＴＣＢ来改善硝胺推进剂的燃烧性能。结果表明这种催化剂的催化效果很好,在本试验配方条件下,硝胺推进剂常温下在７．８～１７．７ＭＰａ压力范围内,压力指数降为０．３７８,１７．７ＭＰａ压力下燃速升为２８．３２ｍｍ／ｓ。     

六硝基六氮杂异伍兹烷的机械撞击感度

用不同工艺条件将γ-HNIW转晶为ε-HNIW,得到不同晶癖的ε-HNIW;采用不同包覆剂对ε-HNIW进行包覆研究,得到了表面改性的ε-HNIW;对两类样品进行了机械撞击感度研究。结果表明,近似平行四边形、颗粒较均匀、碎晶少的样品感度最低;颗粒细小、细针状、碎晶多的HNIW样品感度高,石蜡、丁腑橡胶可良好钝感HNIW,聚碳酸酯、丙烯腈-丁二烯一苯乙烯共聚物包覆的样品的感度较高。     

催化剂对浇铸RDX-CMDB推进剂燃烧性能影响的研究

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。     

纳米铝粉对硝胺炸药热分解催化性能的影响

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.     

固体推进剂燃烧波结构研究

设计了一套分析燃烧波结构的数值计算方法,可以利用热偶数据有效地分析均质推进剂固相反应的细节,为了解固体推进剂机理提拱了一种重要的手段;提出了均质推进剂也没有明显的固气界面的观点,因而也无表面温度可言;设计了固相反应热计算模型,提出了固相反应机理的观点,并指出压力不同固相反应机理基本相同,但固相放热程度不同;提出Π型热偶不宜测量非均质推进剂燃烧波结构的观点。     

含黑索今酮的火药热分解及燃烧性能研究

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。     

Effects of an Organic‐inorganic Nanocomposite Additive on the Combustion and Erosion Performance of High Energy Propellants Containing RDX

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.     

包覆奥克托今颗粒的燃烧性能

采用聚合物材料和一些键合剂对ＨＭＸ表面进行了包覆,并研究了包覆材料对ＨＭＸ燃烧性能的影响,试验表明,聚合物材料将降低度系数而不盼子键合剂对ＨＭＸ燃性能的影响不大。     

Effect of Initial Oxide Layer on Ignition and Combustion of Boron Powder

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 x_0, 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     

Influence of an Electric Field on the Burning Behavior of Solid Fuels and Propellants

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.