HTPE钝感推进剂的子弹撞击和快速烤燃特性

理论计算了HTPE钝感推进剂(PET/AP/Al质量比为18∶64∶18)的质量比冲、特征速度和绝热燃烧温度,测试了推进剂的爆热和密度,依据GJB772A-97 601.2方法和GJB772A-97 602.1方法,测定了推进剂的机械感度,并与HTPB推进剂进行了比较,评估了HTPE钝感推进剂的子弹撞击和快速烤燃特性。结果表明,HTPE推进剂在6.86MPa下的理论比冲为268.0s,实测爆热为7456J/g,实测密度为1.812g/cm~3,均大于HTPB推进剂;HTPE推进剂在低压下(1MPa)可稳定燃烧,并且具有较低的燃速压强指数,在1～18MPa下n≤0.42;推进剂具有较低的外界刺激感度,其中摩擦感度为0,撞击感度(特性落高H_(50))大于77cm,12.7cm子弹撞击试验和快速烤燃试验均表现为燃烧反应,具有较低的易损特性。     

纳米催化材料与超细高氯酸铵的均匀复合及对复合改性双基推进剂的增速降感研究

为了提高复合改性双基推进剂的燃速，采用超音速气流粉碎技术将纳米催化材料(纳米亚铬酸铜、纳米氧化镉)原位分散于超细高氯酸铵(AP)表面，制备出纳米催化材料/超细AP复合物，并应用于改铵铜(GATo)高燃速改性双基推进剂。采用扫描电子显微镜(SEM)、差示扫描量热测试(DSC)、机械感度测试、静电火花感度测试等方法对纳米催化材料/超细AP复合粒子进行了分析表征，对制得的含纳米催化材料/超细AP复合粒子的GATo推进剂分别进行了燃烧性能、力学性能、机械感度和安定性研究。结果表明，在超音速气流粉碎力场作用下，在实现AP超细化的同时，实现了纳米催化材料在其表面的原位均匀分散，既提高了超细AP的热分解速率，又降低了超细AP的机械感度。与空白GATo推进剂相比，含有纳米催化材料/超细AP复合粒子的GATo推进剂燃速从55mm/s提升至70.27mm/s(20℃、10MPa),增幅达27.8%,力学性能和安定性基本保持不变，摩擦感度从95%降至80%,撞击感度特性落高值从13.9cm提高到14.7cm,实现了CMDB推进剂的高燃速与低感度的有效平衡。     

含相稳定硝酸铵CMDB推进剂的机械感度和燃烧性能

通过测试撞击感度、摩擦感度和燃速,研究了含相稳定硝酸铵(PSAN)的改性双基(CMDB)推进剂的燃烧性能和机械感度。结果表明,PSAN可改善CMDB推进剂的机械感度;用PSAN作氧化剂,其推进剂的燃速低于RDX作氧化剂的燃速,压强指数高于后者的压强指数;1～5MPa压力范围内随PSAN在配方中含量的增加,推进剂的燃速降低,压强指数升高。     

LX-04炸药大隔板试验的数值模拟

为研究不同条件下LX--04（HMX／氟橡胶／85／15）大隔板试验（LSGT）的冲击波感度G。,运用ANSYS／LS．DYNA对整个爆炸冲击波传爆过程进行了数值模拟,观察了LSGT中爆轰冲击波的传播过程,分别讨论了主发炸药PE4、TNT、B炸药产生的爆轰波经过有机玻璃隔板、铝隔板、钢隔板衰减后的冲击波压力变化情况,最终找出了3种不同主发炸药和3种隔板下LX-04冲击波感度G50。同时,定性地分析了3种隔板对爆炸冲击波的衰减系数。其中,铝隔板的衰减系数最大,有机玻璃隔板的衰减系数最小。     

湿热条件下复合固体推进剂老化特性研究

为研究HTPB(端羟基聚丁二烯)、NEPE(硝酸酯增塑聚醚)2种复合固体推进剂在湿热贮存环境中的老化机理,开展了77%相对湿度、60℃和77%相对湿度、20℃条件下的贮存老化试验,实时监测了推进剂最大抗拉强度、冲击感度、邵氏硬度、热老化过程中质量的变化规律。研究发现:2种推进剂在湿热贮存环境下,最大抗拉强度随老化时间的延长持续下降;黏合剂分解是造成2种推进剂硬度变化的主要因素,且HTPB推进剂内部黏合剂受影响更大;NEPE推进剂冲击感度随老化时间增加逐渐降低,而HTPB推进剂则存在感度值回升现象;2种推进剂在湿热环境中质量均增大,且HTPB推进剂吸湿性更强。     

固体推进剂对射流刺激的易损性响应

以空心装药为标准射流源,研究了3种典型固体推进剂在空心装药射流冲击下的易损性响应特性,分析了配方、射流源的冲击方向(轴向或径向)、装药尺寸等对固体推进剂易损性响应的影响。结果表明,推进剂对轴向射流刺激的响应程度大于径向响应;在千克级药量和长径比为4∶1和1∶1条件下,3种典型推进剂对射流刺激的响应程度差别不大,且均有较强反应发生;HTPB复合推进剂、改性双基推进剂、NEPE推进剂的反应等级依次为爆炸、部分爆轰和部分爆轰。     

添加剂对B炸药安全和爆轰性能的影响

在B炸药中分别添加质量分数1%和3%的123树脂/1DES黏结剂或质量分数5%固化系数为0.6和0.8的HTPB/MDI黏结剂,制备了4种改性B炸药。用大药片落锤撞击试验、电探针和锰铜压力计分别测试了其撞击感度、爆速和爆压,用VLWR程序计算了爆轰性能。结果表明,添加123树脂/DES黏结剂后,改性B炸药的撞击感度降低;添加不同固化系数的HTPB/MDI黏结剂后,改性B炸药的撞击感度升高;添加123树脂/DES和HTPB/MDI后,改性B炸药的密度、爆速和爆压降低,而且添加量越大,其爆速和爆压降低越大。爆速和爆压的计算值与实验值接近。     

双(二羰基环戊二烯铁)对高氯酸铵热分解性能的影响

采用SEM(扫描电镜)、XPS(X射线光电子能谱)等表征了双(二羰基环戊二烯铁)(简称Fe1)的微观形貌和Fe元素的价态,采用摩擦感度、静电感度和冲击感度测试了Fe1与推进剂相关组分HTPB(端羟基聚丁二烯)、AP(高氯酸铵)、HMX(奥克托今)的安全性能,采用DSC-TG(差热–热重)研究了AP/Fe1及HTPB/Al/AP/HMX/Fe1推进剂的催化热分解性能。结果表明:Fe1的pH为5.79,密度为1.76g/cm~3,其中Fe为零价;Fe1与推进剂相关组分HTPB、AP、HMX的安全性能良好;Fe1催化AP的热分解,AP的转晶峰温提前了2℃,低温分解峰和高温分解峰分别提前了6℃和54℃;在HTPB/Al/AP/HMX推进剂中添加质量分数为5%的Fe1,AP的高温分解峰提前48.1℃;Fe1具有大幅提高HTPB推进剂燃速的潜力。     

六氯环三磷腈对RDX-CMDB推进剂性能的影响

为考察六氯环三磷腈(HCCT)作为降速剂对RDX-CMDB推进剂燃速、安定性、爆热、机械感度、力学性能的影响,测试了HCCT与RDX-CMDB主要组分的相容性,并采用靶线法、甲基紫法、绝热法等测试了3种不同HCCT含量的RDX-CMDB推进剂的性能。结果表明,HCCT与RDX-CMDB推进剂主要组分NC+NG及RDX的相容性较好,HCCT的加入使推进剂在2~6MPa压强下燃速降低,燃速压强指数升高,爆热降低,摩擦感度和撞击感度降低,抗拉强度及延伸率基本不变,对推进剂的化学安定性没有影响。     

丁羟推进剂的应用发展

本文介绍了端羟聚丁二烯(HTPB)推进荆的发展概况,简述了端羟聚丁二烯(HTPB)粘合剂及其性能.叙述了丁羟推进剂的进展及应用情况,指出了高能量、高燃速和无烟丁羟推进剂研究方向和在此过程中所要解决的关键问题.     

RDX-CMDB推进剂燃速温度敏感系数的实验研究

为了揭示RDX-CMDB推进剂中各常见组分对其燃速温度敏感系数的影响规律,制备了一系列含RDX、铝粉及燃烧催化剂的CMDB推进剂样品。采用氮气靶线法测得其在2~14MPa下的燃速温度敏感系数(σp)。讨论了RDX含量、铝粉、燃烧催化剂对RDX-CMDB推进剂燃速温度敏感系数的影响。结果表明,提高工作压强、增加RDX含量、添加燃烧催化剂均有助于降低RDX-CMDB推进剂在一定初始条件下的燃速温度敏感系数。配方中引入铝粉后可降低中低压下RDX-CMDB推进剂的燃速温度敏感系数,且燃速温度敏感系数几乎不随压强变化而变化。选用含邻苯二甲酸铅和没食子酸铋锆作燃烧催化剂,均可在2~10MPa下降低RDX-CMDB推进剂的燃速压强指数,同时降低燃速温度敏感系数。     

撞击作用下螺压复合改性双基推进剂药片的响应

采用落锤仪研究了螺压复合改性双基(CMDB)推进剂药片在撞击作用下发生分解、燃烧或爆炸响应的临界值,获得了不同RDX含量、样品厚度及样品温度对推进剂在撞击作用下响应临界值的影响规律。结果表明,在推进剂中引入RDX不会增加推进剂对撞击刺激的敏感程度;RDX的质量分数为0~54.5%时,随着RDX含量的增加,推进剂药片对撞击刺激的敏感程度逐渐降低;样品厚度为1、2、3mm时,随着样品厚度的增加,推进剂药片对撞击刺激的敏感程度显著降低;推进剂在70℃时对撞击刺激比25℃时更加敏感。     

Burning Behavior of Composite Propellant Containing Fine Porous Ammonium Perchlorate

A fine porous ammonium perchlorate (FPAP) was prepared by the spray-drying method. The burning behavior of a propellant containing FPAP was investigated and compared with that of a propellant containing a fine ammonium perchlorate without porosity (FAP), of which the mean diameter was almost the same as that of FPAP. The results are as follows: (1) The burning rate of the propellant containing FPAP increases with increasing FPAP content. (2) When the propellants containing FPAP or FAP have the same composition, the burning rate of the propellant containing FPAP is larger than that of the propellant containing FAP at various pressures. (3) The temperature sensitivity of a propellant containing FAP is relatively constant at various pressures. However the temperature sensitivity of the propellant containing FPAP decreases with increasing pressure. (4) It was found that the differences in the burning behavior of the propellant containing FPAP and the propellant containing FAP are caused by the porosity of FPAP.     

纳米ZnO立方体催化AP热分解及其在HTPE推进剂中的应用

为改善高氯酸铵(AP)的性能,从而改善复合固体推进剂的燃烧性能,采用AP辅助的金属有机骨架结构(MOF)热分解法合成纳米ZnO立方体催化剂(n-ZnO/cube);采用XRD、FESEM、TEM等对其形貌进行了表征,分析了其比表面积和孔径分布;采用TG-DTA分析了其对AP热分解的影响;将其加入到HTPE推进剂中,测试了其对推进剂工艺性能、安全性能、力学性能及燃烧性能的影响。结果表明,n-ZnO/cube催化剂具有大的比表面积(70.5m2/g)和大量的孔道结构,将AP热分解的高温分解峰从413℃降至279℃,放热量从584J/g增至1520J/g,分解活化能从151.1kJ/mol降至65.3kJ/mol;将质量分数2%的n-ZnO/cube加入到HTPE推进剂中,推进剂的燃速(20℃,6.86MPa)从12.01mm/s提高到16.16mm/s,工艺性能、安全性能、力学性能、燃速压强指数(0.42,20℃,3~16MPa)、燃速温度敏感系数(2.02×10^-3℃^-1,-55~70℃,6.86MPa)均未受到明显影响,表明纳米ZnO立方体结构对AP热分解表现出良好的催化性能,是HTPE推进剂的一种具有潜力的燃烧调节剂。     

低温感硝胺火药定容燃烧特性研究

采用小粒药作为冲击药在密封爆发器中研究了低温感（LTSC）高能硝胺包覆火药的燃烧特性,比较了不同温度,不同包覆层厚度条件下包覆药的燃烧特点,为判断包覆药是否具有低温感效果提供了实验基础。     

Enhancement of Aluminum Reactivity to Achieve High Burn Rate for an End Burning Rocket Motor

Aluminum is used in solid propellants to increase the specific impulse (I _sp). It is desirable to have high propellant loading in any stage as it reduces the structural coefficient and an end burning grain is known to be the one with the highest propellant loading. As aluminum combustion is a slow process, the time available for aluminum combustion in an end burning configuration will be very small at the start of the combustion process. This demands an increase in the reactivity of the aluminum. This study is built on the fact that mechanical activation of aluminum powder with PTFE (poly‐tetra‐flouro‐ethylene) enhances the reactivity of aluminum powder. This study also deals with the use of this activated aluminum powder in conjunction with various other methods to enhance the burn rates of the solid propellant. The temperature sensitivity was also measured. Based on these results, new designs with end burning grains for the third stage of Polar Satellite Launch Vehicle (PSLV) and for the second and third stage of Pegasus launch vehicle have been proposed to increase the payload capacity. With this new design, it is seen that the payload can be increased by 12.7 % and 17.6 % for PSLV and Pegasus, respectively. The novelty of this design is that with no changes to any other hardware of the above two systems the increase in payload can be achieved.     

Combustion Mechanism of Azide Polymer

The combustion wave structure and thermal decomposition process of azide polymer were studied to determine the parameters which control the burning rate. The azide polymer studied was glycidyl azide polymer (GAP) which contains energetic – N₃ groups. GAP was cured with hexamethylene diisocyanate (HMDI) and crosslinked with trimethylolpropane (TMP) to formulate GAP propellant. From the experiments, it was found that the burning rate of GAP propellant is significantly high even though the adiabatic flame temperature of GAP propellant is lower than that of conventional solid propellants. The energy released at the burning surface of GAP propellant is caused by the scission of N N₂ bond which produces gaseous N₂. The heat flux transferred back from the gas phase to the burning surface is very small compared with the heat generated at the burning surface. The activation energy of the decomposition of the burning surface of GAP propellant, E_s, is determined to be 87 kJ/mol. The burning rate is represented by r = 9.16 × 10³ exp(–E_s/RT_s) where r (m/s) is burning rate, T_s (K) is the burning surface temperature, and R is the universal gas constant. The observed high temperature sensitivity of burning rate is correlated to the relationship of (∂T_s/∂T₀)_p = 0.481 at 5 MPa, where T₀ is the initial propellant temperature.     

发射药用聚二甲基丙烯酸乙二醇酯钝感包覆层性能研究

为研究高分子钝感发射药改变燃烧规律的机理，研究了其涂覆层的聚合条件。通过改变聚合方式、温度、时间、引发剂、聚合界面的方法，探讨了涂覆层的聚合工艺；通过材料试验机试验和热分解试验，研究了聚二甲基丙烯酸乙二醇酯（PEDMA）涂覆层在不同温度下的力学性能及其热分解规律。研究发现，采用合适的工艺可制得钝感发射药；PEDMA在单基药表面形成钝感层且存在过渡的互穿网络结构，涂覆层和基体药的力学性能受温度影响差别较大，这一特性是高分子钝感药温度系数低的原因之一。热分解研究表明，PEDMA钝感发射药改变了传统单基药的燃烧规律，具有延迟点火和变燃速的特点。