过渡金属有机酸盐M对太根发射药燃速压力指数的影响

将过渡金属有机酸盐M作为催化剂引入太根发射药中,通过密闭爆发器实验测试了催化剂M对太根发射药燃速压力指数降低的效果,并利用发射药能量示性数软件计算了含催化剂M的太根发射药的火药力和爆温。结果表明,合适的催化剂M含量可以降低测试压力范围内太根发射药的燃速压力指数,添加质量分数为1.5%的催化剂对太根发射药燃速压力指数的降低作用最明显,此时火药力下降不到1%,对发射药能量影响较小。     

RDX改性双基球形小粒药的燃烧特性

讨论了改性双基球形小粒药中RDX颗粒的分布和RDX热分解的特点,提出了RDX改性双基球形小粒药的燃烧机理。通过密闭爆发器实验测定了RDX改性双基小粒药的燃烧特性,并对实验结果进行了理论分析。结果表明,改性双基球形小粒药中RDX与双基火药基体的分解是各自独立进行的;随着压力的升高,改性双基小粒药的燃速将大于改型双基小粒药的燃速。     

不同催化剂对降低双基火药燃速压力指数效果的影响

为探讨降低火药燃速压力指数的技术途径,进行了催化剂降低双基火药燃速压力指数的研究.选择9种催化剂,测定了含有催化剂双基火药的燃速压力指数,同时对其进行了分段处理.探讨了不同催化剂在不同压力段对降低双基火药燃速压力指数的规律.结果表明,不同催化剂在不同压力段对降低双基药压力指数有不同的效果,总趋势是低压段效果较明显,在研究的9种催化剂中,纳米CuO和Pb3O4催化剂能够明显降低双基火药燃速压力指数.     

火药燃速在不同条件下的规律分析

为了深入研究火药燃速在不同条件下的规律,采用密闭爆发器实验和分段数据拟合函数法,通过DY630和SF-3两种火药的燃速压力指数和燃速系数变化规律来分析燃速的变化规律,并与经典理论进行对比分析。分析表明,多孔粒状药的燃速压力指数比单孔管状药的燃速压力指数要小:实际燃速的u-P曲线中的直线阶段(主燃烧阶段)为经典理论的u-p曲线。     

AP-CMDB 推进剂稳态燃烧性能计算研究

建立了一个ＡＰ－ＣＭＤＢ推进剂稳态燃烧模型。该模型可用于ＡＰ－ＣＭＤＢ推进剂和经典双基推进剂燃速特性的模拟计算，其计算结果与文献值相符合，说明该模型是合理、可行的。ＡＰ－ＣＭＤＢ推进剂计算结果表明，ＡＰ粒径减小，ＡＰ含量增加，推进剂燃速升高；而含能粘结剂——ＤＢ母体的含能程度越高，即ＮＧ含量增加，或ＮＣ的硝化度加大，都有利于提高推进剂的燃速。     

含铜催化剂对RDX/AP/HTPB推进剂燃烧特性的影响

采用热分析方法，研究了五种新型含铜催化剂对ＡＰ、ＡＰ／ＲＤＸ热分解特性的影响，从中筛选出两种催化效果比较好的催化剂。进一步研究了它们对ＡＰ／ＲＤＸ／ＨＴＰＢ推进剂燃速及燃速压强指数的影响。结果表明：这两种催化剂对提高燃速，降低压强指数有明显效果，经适当组合，可进一步提高燃速，降低压强指数。     

双基系推进剂用生态安全的含铋催化剂

综述了生态安全的含铋催化剂对双基和ＲＤＸ－ＣＭＤＢ推进剂燃烧性能的影响,分析比较了铋化物和铅化物的催化作用。分析结果表明,粒度小、分散性好的铋化物能够取代生态安全性差的含铅燃速催化剂用于双基系推进剂中。     

硝酸异丙酯对单基发射药燃烧性能的影响

为研究硝酸异丙酯对单基发射药燃烧性能的影响,用密闭爆发器测试了加入硝酸异丙酯后单基发射药的燃烧性能。通过分析p-t曲线,得到最大压力、燃烧时间、气体生成猛度、压力全冲量、火药已燃百分数、火药力和余容等燃烧特性参数以及燃烧速度与压力之间的关系。结果表明,硝酸异丙酯使发射药的燃烧速度加快,燃烧时间缩短,燃速系数增大,压力指数减小。     

黑索今、奥克托今和有机阻燃剂混合物的热分解研究

利用差热分析（ＤＴＡ）技术研究了黑索今（ＲＤＸ）、奥克托今（ＨＭＸ）和某些阻燃型添加剂（ＦＰＡ）二元混合体系的热分解唯象动力学,求得了唯象动力学能量Ｅ、Ａ、ｋ,同时分析了４００℃时,不同压力下反应速率常数ｋ与燃速抑制系数Ｋ间的线性关联性。     

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。     

新型高能高强度JMZ发射药的燃烧特性

为探索混合硝酸酯增塑的聚醚聚氨酯黏合剂体系的新型发射药的燃烧性能,通过密闭爆发器常规实验和高压实验．研究分析了JMZ发射药在不同压力范围的燃烧特性。结果表明,JMZ发射药在低压下的燃速压力指数较大,具有高含量RDX硝胺发射药的共同特征,但在高压下的燃速压力指数逐渐变小,与制式发射药相当,在燃速压力指数的变化过程中不存在明显的转折现象。另外,JMZ发射药在起始阶段表现出了良好的燃烧渐增性,对身管武器的应用是十分有利的。     

LOVA发射药点火燃烧性能

制备了含有两种不同黏结剂的低易损性发射药(即LOVA发射药),并应用点火燃烧模拟装置与密闭爆发器对其点火燃烧性能进行了研究。结果表明,LOVA发射药难点火,但在点火药中添加高氯酸铵后可有效改善LOVA发射药的点火性能。LOVA发射药燃烧具有燃速系数低、燃速压力指数高等特点。     

NGu对含RDX硝胺发射药燃烧性能的影响

为从微观的角度研究NGu对含RDX的硝胺发射药燃速压力指数改变的影响,采用改进的小型点火燃烧模拟装置,在35MPa左右对几种发射药进行低压中止燃烧实验.通过SEM电镜观察发射药在低压下燃烧的表面状况.结果表明,在硝胺发射药的燃烧过程中,NGu在燃烧表面形成较厚的熔融层,抑制了RDX的爆燃;RDX的爆燃与燃烧表面熔融层之间的"均衡状态"影响发射药燃速压力指数的变化,当RDX与NGu质量比小于1时,燃速压力指数明显降低;当RDX和NGu同时存在时,发射药的燃烧表面有针状晶体生成.     

含1,3,3-三硝基氮杂环丁烷CMDB和NEPE推进剂的燃烧性能和热行为

利用燃速和火焰结构测试、TG-DTG和高压DSC实验分别研究了含1．3，3-三硝基氮杂环丁烷(TNAZ)的两类(TZ-CMDB和TZ-NEPE)推进剂的燃烧性能和热行为，发现了TNAZ对推进剂燃速、压力指数和火焰结构的影响及高压下TNAZ对上述两类推进剂中其它含能组分分解的影响，并得出常压下TZ-CMDB和TZ-NEPE推进剂受热时，TNAZ挥发和分解的温度范围为58～190℃。     

复合催化剂对Al/HMX/CMDB推进剂安定性的影响

含有复合催化剂的Al/HMX/CMDB推进剂样品,在放置3~4周后,爆热、燃速下降,压强指数升高。为找到具体原因,对推进剂试样进行了燃烧性能、真空安定性及DSC热分解实验,并对实验结果进行了系统分析。结果表明:复合催化剂中超细的SnO2具有较强的催化活性,催化推进剂在常温下进行热分解,最终导致推进剂安定性、爆热、燃速下降,压强指数升高。推进剂性能的恶化,严重影响其正常使用。     

Synthesis,Characterization, and Combustion Catalytic Activities of Copper(II) and Lead(II) Salts of p‐Nitrocalix[n]arenes (n=4, 6, 8)

Six copper(II) and lead(II) salts of p‐nitrocalix[n]arene (n=4, 6, 8) were synthsized and characterized. The DSC curves of all salts showed exothermic decomposition. Sensitivity studies revealed that all the salts with the exception of the lead salt of p‐nitrocalix[6]arene (NCPb6) are relatively insensitive materials. Investigations of the catalytic activities showed that most of the salts displayed high activities in thermal decomposition of NC‐NG and RDX. As evaluated in this work, the salts enhanced the burning rates of both double base (DB) and RDX‐component modified double base propellants. The best catalytic effect was obtained with NCPb6, which increased the burning rate of the DB propellant to the order of about 200 % (2–6 MPa) and 103–198 % (8–20 MPa) while decreasing the pressure index (n) to 0.22 (20–22 MPa).     

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.     

含N,N-二硝基哌嗪无烟改性双基推进剂的燃烧性能

以CMDB推进剂为基础,用N,N-二硝基哌嗪(DNP)替代推进剂中的RDX,研究了DNP含量、燃烧稳定剂(CaCO3、TiO2、MgO及Al2O3)、燃烧催化剂(铅盐、铅盐/铜盐、铅盐/铜盐/炭黑)对DNP-CMDB推进剂燃烧性能的影响。结果表明,DNP可明显降低无烟CMDB推进剂的燃速,当DNP完全替代RDX时,在18MPa压强下推进剂的燃速降低约68%;铅盐/铜盐/炭黑燃烧催化剂复配体系能够有效降低DNP-CMDB推进剂的燃速压强指数,使其出现平台燃烧效应。     

Thermal Decomposition of BAMO/HMX Propellants

Thermal decomposition of BAMO [bis(azidomethyl)oxetane/tetrahydrofuran copolymer]/HMX composite propellants was studied by isothermal TGA (thermogravimetric analysis) and DSC (differential scanning calorimetry) in helium atmosphere, which was showing overall two steps first-order kinetics. The effects of cross-link ratio on the accelerated aging of the BAMO/HMX propellants were also measured with infrared spectroscopy and gas chromatography. The accelerated aging was conducted at 347 K for several weeks. BAMO/HMX propellants for a very low cross-link ratio made the cavity between HMX and BAMO binder by N₂, CO₂, and H₂O evolutions during accelerated aging. An exotherm, generated by the decomposition of azide binder, initiated and accelerated the thermal decomposition of HMX. The burning rate of BAMO/HMX propellant was larger than those of BAMO binder and HMX, respectively. However, the propellant could not maintain the combustion at low pressure, at which its burning rate was equal to that of BAMO binder.     

Influence of Particle Size on the Combustion of CL‐20/HTPB Propellants

The effect of nitramine particle size on the combustion behavior of inert binder based propellants has been extensively studied for RDX and HMX, but not CL‐20. Although materials such as RDX and HMX are useful for particular combustion applications, CL‐20 has a greater potential to improve the oxygen balance and energy density of a propellant. The current work investigates the effect of CL‐20 particle size on the combustion of CL‐20/HTPB propellants down to submicrometer sizes. An influence of particle size on the burning rate and combustion mechanism is reported. The 30 micrometer formulation burning rate data showed evidence of convective burning specifically at higher pressures, but the pressure dependence was comparable to neat CL‐20 at pressures below 8 MPa. A change in the combustion mechanism of the submicrometer formulation as a function of pressure was determined to be a result of the interaction of the propellant flame and the combustion residue. Data suggested that at low pressures diffusion in terms of active cooling was dominant for the submicrometer formulation. Higher pressure data for both the submicrometer and 3 micrometer formulations suggest the degree of active cooling is decreased as the burning rate pressure exponent is near 0.5 for both propellants. The indirect evidence for the presence of a melt layer for CL‐20 propellants is discussed.