国内简讯

过氧化氢在火箭推进剂和喷射气源中的应用前景我国新一代运载火箭的基本目标之一是采用无毒、无污染推进剂。使用过氧化氢 /煤油或醇类推进剂其优点是无毒 ,燃烧产物洁净 ,只要解决自燃点火的关键技术 ,就可获得极大推广应用价值。我国研制的DF 1和DF 2导弹发动机采用 78%的过氧化氢经燃气发生器分解的产物作为驱动涡轮的工质。过氧化氢 /煤油 (或醇类 )推进剂将主要推广应用于航天姿控发动机及载人飞船上 ,还可应用于军事卫星、运载火箭和反弹道导弹 ,将来甚至还可推广应用于民用汽车发动机。超纯过氧化氢生产上海哈勃化学技术有限公司研…     

国外鱼雷热动力推进剂应用与发展趋势

简要介绍了国外鱼雷热动力推进剂的种类和能量密度,详细综述了柴油(煤油)/H_2O_2、OTTO-Ⅱ、HAP(高氯酸羟胺)/OTTO-Ⅱ/海水、水反应金属燃料等鱼雷热动力推进剂的性能及应用,并展望了鱼雷热动力推进剂未来发展趋势。     

NC/Bu-NENA基推进剂性能研究(Ⅰ):推进剂能量及燃烧性能

为了研究丁基-硝氧乙基硝胺(Bu-NENA)对NC基推进剂能量及燃烧性能的影响,通过俄罗斯Real软件计算了Bu-NENA对推进剂的能量性能的影响;通过吸收-压延的方法制备了推进剂样品,测试了推进剂的密度、爆热、比容、点火延迟、燃速,计算了压强指数;通过燃烧波、火焰照片以及熄火表面探讨了Bu-NENA对推进剂燃烧性能影响的机理。结果表明,在NC基推进剂中Bu-NENA替代NG使能量下降,但是产气量增加,使推进剂的燃速大幅度下降,2MPa下燃速降幅75%以上,20MPa下燃速降幅64%以上;压强指数提升,NC/NG基推进剂用部分催化剂可能对NC/Bu-NENA基体系失效;推进剂的点火延迟时间增加;推进剂的燃速大幅度降低的原因可能是因为Bu-NENA在燃烧时挥发吸热以及燃温降低带来的热反馈降低。     

新型绿色液体推进剂研究进展

对近年来国内外出现的新型绿色（无毒、对环境友好）液体推进剂进行了评述。硝酸羟铵基单组元推进剂具有冰点低、密度比冲高、安全无毒的特点,适用于小卫星和上面级,催化分解技术还有待深入研究;二硝酰胺铵基单组元推进剂比冲高于硝酸羟胺基单元推进剂,发动机脉冲工作能力可与无水肼发动机相媲美,但目前发动机预热温度和燃烧室温度都过高;高浓度过氧化氢／醇基推进剂比冲为常规推进剂比冲的93％,密度比冲为102％;过氧化氢／叠氮胺类不但密度比冲高,而且可实现自燃;一氧化二氮基双组元推进剂在微推进系统中有广泛的应用前景;原子推进剂以其优良的比冲性能将给航天运载器带来革命性的飞跃,但对低温技术提出了挑战。     

光电子能谱仪用于改性双基推进剂晶析的研究初探

改性双基推进剂通过加入各种添加剂来提高推进剂的能量或改善其烧燃性能。然而,各种添加剂加入推进剂后可能出现的晶析问题,又会影响推进剂的弹道特性及点火、密度、包覆等性能。所以在进行改性双基推进剂配方设计时,晶析问题是应该考虑的。     

光电子能谱仪用于改性双基推进剂晶析的研究初探

改性双基推进剂通过加入各种添加剂来提高推进剂的能量或改善其烧燃性能。然而,各种添加剂加入推进剂后可能出现的晶析问题,又会影响推进剂的弹道特性及点火、密度、包覆等性能。所以在进行改性双基推进剂配方设计时,晶析问题是应该考虑的。     

铝镁贫氧推进剂的点火性能

为研究镁铝富燃料固体推进剂组分对点火性能的影响,采用改进的靶线法燃速测试系统对多种含镁铝富燃料固体推进剂在常压和加压下进行了通电金属丝点火性能的对比实验。被测试推进剂的镁铝合金含量为20%～40%,或者同时含镁铝合金及硼,氧化剂含量为30%～53%。实验表明,在固定外界输入热源的情况下,推进剂的点火性能主要与氧化剂含量和粒度有关;金属的含量和种类也有一定的影响;催化剂对点火延迟时间影响很小;压强对此种点火方式几乎无影响。该点火延迟测试方法简单易行,并具有一定的可靠度,适于配方调试。     

HTPB/AP复合推进剂冲击波点火实验研究

根据增效射孔器的实际作用,以AP-丁羟（HTPB/AP）复合推进剂为研究对象,利用隔板试验研究了冲击波对AP-丁羟复合推进剂的点火性能,结果表明,合理控制冲击波强度能够使AP-丁羟复合推进剂可靠点燃,并为其它推进剂的点火提供了一种新方法.     

合金燃料在固体推进剂中的应用

介绍了合金燃料的特点及其制备方法,并对合金燃料在固体推进剂中的应用研究情况进行了综述.认为合金燃料具有点火性能好、点火温度及熔点可调、燃烧效率高等优点,而且对推进剂的燃烧性能有重要影响.其中贮氢合金燃料有较高的生成焓,与推进剂组分有良好的相容性,在高能推进剂中有良好的应用前景.     

丁羟复合推进剂的辐射点火

采用CO2激光点火装置,对丁羟复合推进剂的点火过程进行了实验研究,利用描述固体推进剂物化现象的一维传热模型对复合推进剂的辐射点火特性进行了理论分析。通过最小二乘法拟合实验数据得到了丁羟复合推进剂的点火准则。结果表明,丁羟复合推进剂的点火过程主要包括惰性加热及气相点火过程,惰性加热时间和点火延迟时间随热流密度的增大而减小,且随着热流密度的增大,热流密度的影响逐渐降低。固相传热数学模型能够比较准确地描述复合推进剂的辐射点火特性。     

An experimental study on the hypergolic ignition of hydrogen peroxide and ethanolamine

This paper presents the hypergolic ignition test results of a potential environmentally friendly liquid propellant consisting of hydrogen peroxide oxidizer (with a concentration of 85%) and ethanolamine fuel for use in rocket engines. Open cup drop tests were conducted to study the effect of amount of metal salt catalyst in fuel and the initial temperatures of fuel and oxidizer on the ignition delay time. To test the hypergolic ignition of bipropellant formulation in a real rocket engine environment, a pressure-fed liquid propellant rocket engine (LPRE) was designed and developed. During the tests it was found that the amount of catalyst and the initial temperature of the fuel had a significant effect on the ignition delay of hypergolic bipropellant. However, the oxidizer temperature seemed to have almost no affect on the ignition delay. There was also significant difference between the ignition delay times from open cup tests and those from rocket engine static firings.     

Hypergolic Studies of Ethanol Based Gelled Bi‐Propellant System for Propulsion Application

The experiments conducted in this study examined the hypergolicity and ignition delay of the formulated ethanol gelled fuel and hydrogen peroxide oxidizer bipropellant system. The hypergolicity and ignition delay data for bipropellant system are very important for propulsion applications. It was observed that the ethanol based gelled fuel systems were hypergolic with hydrogen peroxide (90% pure) in a presence of a suitable catalyst. The observed ignition delay was within the range of 10∼50 ms, which was comparable with the existing liquid hypergolic bipropellant systems. Temperature profile also indicated that the hypergolic system attained a very high temperature profile range of 1000 °C to 1400 °C for a very small weight percent of fuel. Experiments conducted with two separate volumes of oxidizer, 14 μl and 50 μl. In both cases the propellant system was fuel rich. It was also observed that the formation of cage in the gel network, which could encapsulate the higher temperature gases and flame in a network, might be a plausible reason for recorded higher ignition delay.     

Assessment of Physico‐Thermal Properties,Combustion Performance,and Ignition Delay Time of Dimethyl Amino Ethanol as a Novel Liquid Fuel

Dimethyl amino ethanol (DMAE) contains both hydroxyl and amino functional groups, which may be introduced as a new liquid fuel with high safety and less toxicity with respect to common high performance liquid fuels. Physico‐thermal properties, combustion performance and ignition delay time of DMAE are compared with the usual high performance liquid fuels as well as ethanol and dimethylamine. Combustion performances of DMAE (specific impulse at sea level) with common liquid oxidizers including white fuming nitric acid (WFNA), inhibited red fuming nitric acid (IRFNA), nitrogen tetroxide (N₂O₄), hydrogen peroxide (H₂O₂), liquid oxygen (LOX), and the mixed oxides of nitrogen (MON) are also evaluated. Maximum and minimum specific impulses of DMAE are obtained with LOX (299.6 s) and WFNA (262.4 s), respectively. Maximum density‐specific impulse is obtained with DMAE‐N₂O₄ bipropellant. The ignition delay time of DMAE with several liquid oxidizers are measured with open cup test method. DMAE‐WFNA and DMAE‐IRFNA bipropellants are hypergolic where their ignition delay times are 26 and 42 milliseconds, respectively.     

Theoretical Evaluation and Experimental Validation of Performance Parameters of New Hypergolic Liquid Fuel Blends with Red Fuming Nitric Acid as Oxidizer

A number of fuel blends based on 3‐carene, norbornadiene, furfuryl alcohol, ethylidene norbornene, and kerosene in different weight proportions have been developed as rocket fuels which exhibit synergistic hypergolic ignition with red fuming nitric acid (RFNA) as oxidizer with low ignition delays (IDs<40 ms). The optimum compositions of fuel blends were determined by measuring ID values of different blends at optimum O/F ratios. Eight selected fuel blends and one neat fuel (ethylidene norbornene) were theoretically evaluated for their performance parameters using NASA‐CEC‐71 software with RFNA as oxidizer at different O/F ratios and at chamber pressure of P_c, 2451.66 and 4903.33 (or 5197.52) kPa, keeping the exit pressure constant at 98.07 kPa. For experimental validation of performance parameters, static firing trials of these fuel blends with RFNA were carried out using 735.5 N thruster at 2451.66 kPa chamber pressure using doublet or triplet impinging stream type of injector. The experimental C* values were compared with theoretically determined C* values to predict combustion efficiencies which were found to be more than 95% in all the cases.     

叠氮胺类燃料合成研究进展

叠氮胺类燃料在喷气燃料、单组元液体推进剂、双组元自燃液体推进剂、凝胶推进剂及航天高能密度推进剂方面具有良好前景,文中介绍了叠氮胺类燃料的6种合成方法.     

液体叠氮燃料应用研究进展

对国外液体叠氮燃料在燃料油、喷气燃料、单组元液体推进剂、双组元自燃液体推进剂、凝胶推进剂、航天高能密度推进剂及固体推进剂中的应用研究进行评述,并指出其发展方向。     

Novel solid hypergolic fuels for hybrid propellants

A new class of compounds, viz., monothiocarbohydrazones, have been found to be hypergolic with anhydrous and red fuming nitric acids. A study of the ignition delays of the various thiocarbohydrazonenitric acid systems as a function of particle size and fuel/oxidizer ratio reveals no significant effect by these parameters. The observed ignition delays have been explained in terms of the chemical reactivity and structure of these compounds.     

高炭粉煤灰浮选脱炭试验研究

高含炭量的粉煤灰是一种不可被直接利用的固体废弃物。为降低高炭粉煤灰的烧失量,对高炭粉煤灰进行脱炭试验研究。本文通过磨矿试验确定高炭粉煤灰原灰最佳磨矿时间为1.25 min;通过浮选药剂制度试验确定磨细高炭粉煤灰最佳浮选药剂制度为仲辛醇用量为4 kg/t,煤油用量为12 kg/t;通过浮选工艺试验,确定磨细高炭粉煤灰最佳浮选工艺为叶轮机转速2 000 r/min、刮泡时间8 min、矿浆浓度120 g/L和单位面积充气量0.30 m³/(m²·min)。通过上述试验,最终可得到烧失量为0.63%,产率为60.64%的脱炭粉煤灰,烧失量可达到Ⅰ级灰要求。