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。     

低铝含量NEPE推进剂燃烧性能研究

研究了铝粉含量为8％的NEPE推进剂。采用配浆浇铸法制备推进剂，并用恒压静态燃速仪测试了推进剂的燃烧性能。考察了NG／DEGDN的比例、AP粒度、HMX粒度对燃速及燃速压力指数的影响。发现增大NG／DEGDN的比例、减小AP粒径或增加细粒度AP含量，将提高NEPE推进剂的燃烧速度，压力指数升高；而HMX粒度降低，NEPE推进剂燃速降低，压力指数降低；不同来源的PbCO3对NEPE推进剂燃烧性能影响很大。     

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。     

超声法测试固体推进剂的燃速

通过连续测量超声脉冲在推进剂中的反射时间,确定推进剂燃烧端面的位移,从而得到推进剂的燃烧速度.研制的测试系统由燃烧室、超声探头、匹配层、压力传感器、超声发射接收单元和计算机数据处理单元组成.试验采用低燃速推进剂.在预增压的条件下,试验压强从3 MPa增加到8 MPa,燃速从4.2 mm/s增加到6.4 mm/s,根据燃速压力曲线分段计算出各自的燃速压强指数.测试系统的超声信号清晰,燃速数据准确可靠.     

新型燃烧稳定剂对浇铸RDX-CMDB推进剂燃烧性能的影响

为选择理想的新型燃烧稳定剂,研究了WB、WC、ZrB2、ZrO2、SiC和BN对浇铸RDX-CMDB推进剂燃速和燃速压力指数的影响。结果表明,6种材料都能降低推进剂的燃速,但降低幅度各有差异;ZrB2、ZrO2和SiC对推进剂燃速的降低作用随其粒度的减小而增大;WB和WC在一定含量下可以降低推进剂18～20.5MPa下的燃速压力指数;只有BN使推进剂的燃烧平台效应消失。     

高氯酸铵(AP)粒度对端羟基聚丁二烯(HTPB)推进剂燃烧特性的影响

本文研究了含铝粉的 HTPB 推进剂中 AP 粒度对推进剂燃烧速度和燃速压力指数的影响。结果表明:AP 粒度越小,推进剂燃烧速度就越高、燃速压力指数亦随之增加,并给出了相应的经验公式。本文应用 Summerfield 粒状扩散火焰模型对 AP 粒度与 HTPB 推进剂燃烧特性的关系进行了讨论。     

高氯酸铵(AP)粒度对端羟基聚丁二烯(HTPB)推进剂燃烧特性的影响

本文研究了含铝粉的HTPB推进剂中AP粒度对推进剂燃烧速度和燃速压力指数的影响。结果表明:AP粒度越小,推进剂燃烧速度就越高、燃速压力指数亦随之增加,并给出了相应的经验公式。本文应用Summerfield粒状扩散火焰模型对AP粒度与HTPB推进剂燃烧特性的关系进行了讨论。     

铜盐和碳黑对微烟NEPE推进剂燃烧性能的影响

通过测定不同压力下推进剂的燃烧性能及熄火表面元素分析,研究了两种铜盐（AD和BC）和3种碳黑对微烟NEPE推进剂燃烧性能的影响.结果表明,适量AD可改善推进剂的燃烧性能,使推进剂在3～20 MPa压力范围内的压强指数降至0.45以下;AD在12～18 MPa压力范围内比等量BC对微烟NEPE推进剂燃烧性能的催化作用弱,这可能与AD所含铜元素在燃面的富集程度小于BC有关.3种碳黑均能改变微烟NEPE推进剂在3～18 MPa压力范围内的燃速.增加乙炔碳黑含量可使推进剂在3～20 MPa压力范围内的燃速提高,压力指数降低.     

NEPE推进剂燃烧性能研究

NEPE高能固体推进剂因其优良的综合性能具有十分良好的应用前景。通过调整氧化剂含量、种类及含能增塑剂用量,对NEPE推进剂的燃烧速度和燃速压力指数进行了调节,燃速在9．3～11．6mm／s(7.0MPa)范围内可调，燃速压力指数由0．61降为0.54。     

硝胺单元推进剂的燃烧性能研究

测定了HMX、RDX和CL-20三种硝胺的热分解行为,对硝胺单元推进剂的能量进行了理论计算,并采用固体推进剂燃烧过程测定系统对硝胺单元推进剂的燃烧性能进行了测定,分析了硝胺单元推进剂的燃烧机理.测试结果表明,CL-20的热分解温度较低,其能量较高,燃烧速度约为mMX的2倍,压力指数与HMX、RDX的压力指数相当.     

适应高压强的HTPB推进剂的燃烧性能

为改善高压强下HTPB推进剂的燃烧特性,研究了碳酸盐复合调节剂、二茂铁衍生物G、高氮化合物M、纳米铝粉和纳米金属氧化物对HTPB推进剂燃烧性能的影响.结果表明,碳酸盐复合调节剂能够降低推进剂的燃速和压强指数;二茂铁衍生物G能够提高推进剂的燃速,同时将推进剂在8.60～17.12MPa下的压强指数降至0.27;高氮化合物也可降低推进剂的燃速和压强指数;将高氮化合物M与二茂铁衍生物G配合使用可将推进剂在8.63～16.48MPa下的压强指数降至0.24; 纳米铝粉和包覆的纳米金属氧化物可明显降低推进剂的燃速压强指数.     

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。     

Combustion Characteristics of a Novel Grain‐Binding High Burning Rate Propellant

The novel grain‐binding high burning rate propellant (NGHP) is prepared via a solventless extrusion process of binder and spherical propellant grains. Compared with the traditional grain‐binding porous propellants, NGHP is compact and has no interior micropores. During the combustion of NGHP, there appear honeycomb‐like burning layers, which increase the burning surface and the burning rate of the propellant. The combustion of NGHP is a limited convective combustion process and apt to achieve stable state. The larger the difference between the burning rate of the binder and that of the spherical granular propellants exists, the higher burning rate NGHP has. The smaller the mass ratio of the binder to the spherical granular propellants is, the higher the burning rate of NGHP is. It shows that the addition of 3 wt.‐% composite catalyst (the mixture of lead/copper complex and copper/chrome oxides at a mass ratio of 1 : 1) into NGHP can enhance the burning rate from 48.78 mm⋅s⁻¹ in the absence of catalyst to 56.66 mm⋅s⁻¹ at P=9.81 MPa and decrease the pressure exponent from 0.686 to 0.576 in the pressure range from 9.81 to 19.62 MPa.     

5‐Amino‐3,4‐dinitropyrazole as a Promising Energetic Material

The nitrogen‐rich energetic compound 5‐amino‐3,4‐dinitropyrazole (5‐ADP) was investigated using complementary experimental techniques. X‐ray diffraction indicates the strong intermolecular hydrogen bonding in 5‐ADP crystals. Compound exhibits low impact sensitivity (23 J) and insensitivity to friction. The activation energy of thermolysis determined to be 230±5 kJ mol⁻¹ from DSC measurements. Accelerating rate calorimetry indicates the lower thermal stability (173 °C) of 5‐ADP than that of RDX, which is probably the main concern about using this compound. 5‐ADP also exhibits good compatibility with common energetic materials (viz. TNT, RDX, ammonium perchlorate), including an active binder. The burning rate of 5‐ADP monopropellant is higher than that of benchmark HMX, while the pressure exponent 0.51±0.04 is surprisingly low. Addition of ammonium perchlorate does not affect the pressure exponent of 5‐ADP, while the burning rate increases. The 5‐amino‐3,4‐dinitropyrazole exhibits a notable combination of combustion performance, low sensitivity, and good compatibility, which renders it as a promising energetic material.     

纳米氧化铅为燃烧催化剂的应用研究

运用红外光谱法研究纳米氧化铅对 HMX固相热分解的影响 ,通过静态靶线法燃速测试仪考察纳米氧化铅在推进剂中的实际应用效果。红外谱峰的变化表明 :氧化铅对 HMX的固相热分解直接起催化作用。通过纳米氧化铅在 NEPE推进剂中的实际应用效果表明 :纳米氧化铅可有效的降低 NEPE推进剂的燃速压力指数。     

高能硝胺发射药的膛内基本燃烧特征

针对高能硝胺发射药在静态下燃速压力指数大的特殊燃烧性能，通过３０ｍｍ高压模拟炮试验，采用与制式单基药相对比的研究分析方法，对高能硝胺发射药在火炮膛内条件下的基本燃烧特征进行了研究分析。     

Ballistic Modification of Nitramine Propellants with Special Reference to NG‐PE‐PCP‐Based High Energy Propellants

The burning rate pressure relationship is one of the important criteria in the selection of the propellant for particular applications. The pressure exponent (η) plays a significant role in the internal ballistics of rocket motors. Nitramines are known to produce lower burning rates and higher pressure exponent (η) values. Studies on the burning rate and combustion behavior of advanced high‐energy NG/PE‐PCP/AP/Al‐ and NG/PE‐PCP/HMX/AP/Al‐based solid rocket propellants processed by a conventional slurry cast route were carried out. The objective of present study was to understand the effectiveness of various ballistic modifiers viz. iron oxide, copper chromite, lead/copper oxides, and lead salts in combination with carbon black as a catalyst on the burning rate and pressure exponent of these high‐energy propellants. A 7–9 % increase in the burning rates and almost no effect in pressure exponent values of propellant compositions without nitramine were observed. However, in case of nitramine‐based propellants as compared to propellant compositions without nitramines, slight increases of the burning rates were observed. By incorporation of ballistic modifiers, the pressure exponents can be lowered. The changes in the calorimetric values of the formulations by addition of the catalysts were also studied.     

HAN-based green propellant, application, and its combustion mechanism

Hydroxylammonium nitrate (HAN)-based solutions have been investigated as candidates for a green monopropellant. However, their high burning rate characteristics have hampered the application. In order to elucidate the mechanism of extremely high burning rates of some HAN-based solutions, the combustion characteristics of HAN-based aqueous solutions are studied. It is found that the role of the two-phase region is very important, and intense boiling of water owing to the superheat mechanism is responsible for the high burning rate. Hydrodynamic instability is taken into account, and the dependence of the instability on pressure is estimated. It is found that the instability is strongly affected by the Markstein number. The HAN-based monopropellant is applied to thrusters of a small-sized experimental mockup of a supersonic aircraft and used in the first free-fall test. Their operation is found to be successful and is described in detail.