Cu–Co–O nano-catalysts as a burn rate modifier for composite solid propellants

Nano-catalysts containing copper–cobalt oxides(Cu–Co–O) have been synthesized by the citric acid(CA) complexing method. Copper(II) nitrate and Cobalt(II) nitrate were employed in different molar ratios as the starting reactants to prepare three types of nano-catalysts. Well crystalline nano-catalysts were produced after a period of 3 hours by the calcination of CA–Cu–Co–O precursors at 550 °C. The phase morphologies and crystal composition of synthesized nano-catalysts were examined using Scanning Electron Microscope(SEM), Energy Dispersive Spectroscopy(EDS) and Fourier Transform Infrared Spectroscopy(FTIR) methods. The particle size of nano-catalysts was observed in the range of 90 nm–200 nm. The prepared nano-catalysts were used to formulate propellant samples of various compositions which showed high reactivity toward the combustion of HTPB/AP-based composite solid propellants. The catalytic effects on the decomposition of propellant samples were found to be significant at higher temperatures. The combustion characteristics of composite solid propellants were significantly improved by the incorporation of nano-catalysts. Out of the three catalysts studied in the present work, Cu Co-I was found to be the better catalyst in regard to thermal decomposition and burning nature of composite solid propellants. The improved performance of composite solid propellant can be attributed to the high crystallinity, low agglomeration and lowering the decomposition temperature of oxidizer by the addition of Cu Co-I nano-catalyst.

Comparison of burn rate and thermal decomposition of AP as oxidizer and PVC and HTPB as fuel binder based composite solid propellants

In the present investigation an effort has been made to understand the thermal decomposition and burn rate characteristics of AP as oxidizer and PVC and HTPB as fuel binder in composite solid propellant. The burning rate study has been carried out at ambient and different pressures of 2.068 Mpa, 4.760 Mpa,6.895 Mpa. The mechanism of thermal decomposition of each composition have also been determined by NETZSCH simultaneous thermal analyser, comprising differential scanning calorimeter(DSC) and thermo-gravimetric analyser(TGA). An effort has been made to study the burn rate and decomposition of fuel binder and oxidizer in presence of Fe_2O_3 and also their overall impact on combustion of propellant.

Humic Acid Effects on Reducing Corn Leaf Burn Caused by Foliar Spray of Urea-Ammonium Nitrate at Different Humic Acid/Urea-Ammonium Nitrate Ratios

Technologies for reducing corn leaf burn caused by foliar spray of urea-ammonium nitrate (UAN) during the early growing season are limited. A field experiment was carried out to evaluate the effects of humic acid on corn leaf burn caused by foliar spray of undiluted UAN solution on corn canopy at Jackson, TN in 2018. Thirteen treatments of the mixtures of UAN and humic acid were evaluated at V6 of corn with different UAN application rates and different UAN/humic acid ratios. Leaf burn during 1 2, 3, 4, 5, 6, 7, and 14 days after UAN foliar spray significantly differed between with or without humic acid addition. The addition of humic acid to UAN significantly reduced leaf burn at each UAN application rate (15, 25, and 35 gal/acre). The reduction of leaf burn was enhanced as the humic acid/UAN ratio went up from 10% to 30%. Leaf burn due to foliar application of UAN became severer with higher UAN rates. The linear regression of leaf burn 14 days after application with humic acid/UAN ratio was highly significant and negative. However, the linear regression of leaf burn 14 days after application with the UAN application rate was highly significant and positive. In conclusion, adding humic acid to foliar-applied UAN is beneficial for reducing corn leaf burn during the early growing season.

Burning rate analysis of laser controlled 5-aminotetrazole propellant

As an innovative propulsion technique, laser augmented chemical propulsion(LACP) seems superior to the traditional ones. However, the corresponding combustion theories have still to be ascertained for LACP. Burning rate of 5-aminotetrazole(5-ATZ) propellant has been studied by testing pressed samples under different combustor pressures and laser powers. Based on micro computed tomography(Micro CT),an advanced thickness-over-time(TOT) method to characterize the regression of the produced nonplanar burning surface is established. Because of a shell structure covering the combustion surface,the burning rate of the implemented 5-ATZ propellant is not constant during laser ablation. Resorting to functional fitting, a new law of non-constant burning including the effect of the observed unique burning surface structures is proposed. Accordingly, applicable combustion conditions of 5-ATZ based propellants have been preliminarily speculated for future research activities.

Effect of Burn-off Rate on the Microstructure and Mechanical Properties of the Friction Welded Joint

The effect of the burn off rate on the structure and mechanical properties in the friction welded joint of low alloy constructional steel 35CrMo is studied in this paper. The results show that the increase in the burn off rate and deceleration time of friction welding can improve the toughness of the weld. The mechanism of improving the toughness of the weld is the finer grain size and the lower hardness of the weld. In this paper the microstructure of the joint is also analysed . The fine granular structure in the area near the weld has been studied by TEM.The results indicate that the strengthening mechanism of the weld metal is the high density of dislocation, a number of second island phases and fine grain size. By means of measuring the carbon content of the area near the weld, the effect of the burn off rate on the highest heating temperature of friction welding has also been investigated.

Burning rate and other characteristics of strontium titanate （SrTiO3） supplemented AP/HTPB/Al composite propellants

In a quest of search for a new burning rate modifier for composite propellant, strontium titanate (SrTiO3), a perovskite oxide has been chosen for evaluation in a composite propellant formulation based on its other catalytic applications. Initially, SrTiO3 was characterized for particle size, morphology and material/ phase identification (using XRD). By varying SrTiO3 content in a standard composite propellant, different compositions were prepared and their performance and processing parameters like the end of mix (EOM) viscosity, mechanical properties, density, burning rate, pressure exponent (n-value), etc. were measured. The results reveal that 2% SrTiO3 causes more than 12% enhancement in propellant burning rate (at 70 ksc pressure) in comparison to the standard propellant composition. The pressure exponent also increases to 0.46, whereas the standard composition was having its value as 0.35.

Application of transient burning rate model of solid propellant in electrothermal-chemical launch simulation

A 30 mm electrothermal-chemical(ETC) gun experimental system is employed to research the burning rate characteristics of 4/7 high-nitrogen solid propellant. Enhanced gas generation rates(EGGR) of propellants during and after electrical discharges are verified in the experiments. A modified 0D internal ballistic model is established to simulate the ETC launch. According to the measured pressure and electrical parameters, a transient burning rate law including the influence of EGGR coefficient by electric power and pressure gradient(dp/dt) is added into the model. The EGGR coefficient of 4/7 high-nitrogen solid propellant is equal to 0.005 MW-1. Both simulated breech pressure and projectile muzzle velocity accord with the experimental results well. Compared with Woodley's modified burning rate law, the breech pressure curves acquired by the transient burning rate law are more consistent with test results. Based on the parameters calculated in the model, the relationship among propellant burning rate, pressure gradient(dp/dt) and electric power is analyzed. Depending on the transient burning rate law and experimental data, the burning of solid propellant under the condition of plasma is described more accurately.

Fuel Burning Rate Model for Stratified Charge Engine

A zero-dimensional single-zone double-curve model is presented to predict fuel burning rate in stratified charge engines, and it is integrated with GT-Power to predict the overall performance of the stratified charge engines. The model consists of two exponential functions for calculating the fuel burning rate in different charge zones. The model factors are determined by a non-linear curve fitting technique, based on the experimental data obtained from 30 cases in middle and low loads. The results show good agreement between the measured and calculated cylinder pressures, and the deviation between calculated and measured cylinder pressures is less than 5%. The zerodimensional single-zone double-curve model is successful in the combustion modeling for stratified charge engines.

CALCULATION OF BURNING RATE CHARACTERISTICS IN ACCELERATED FIELD FOR SOME ALUMINIZED SOLID PROPELLANTS

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Effects of Plasticizers,Antioxidants and Burning Rate Modifiers on Aging Performance of the HTPB/HMDI Composite Solid Propellant

The effects of plasticizers,antioxidants and burning rate modifiers on the aging performance of the composite solid propellant based on hydroxyl-terminated polybutadiene(HTPB)/hexamethylene diisocyanate(HMDI)were explored by apply-ing an accelerated aging program for 90 day at 70 ℃. The HTPB propellant matrix with the diisooctyl sebacate(DOS)as plasti-cizers and diisooctyl azelate(DOZ), antioxidants as N,N ′-Diphenyl-p-phenylenediamine(AO) and 2,2′-methylenebis(4-methyl-6-tert-butylphenol)(cyanox 2246)and burning rate modifiers as barium ferrite(BF),copper chromites(CC)and fer-ric oxide(FO)were varied. Results show that sample(S1)which based on DOS decreases the stress value and increases the strain value which considered to be an excellent start for aging program. Sample(S3)containing AO presents the higher resis-tance to oxidation showing the better performance that reflects on increasing the shelf life of the composite solid propellant mo-tor. Sample(S5)which based on BF enhances the ballistic performance among over the other tested two samples. The accelerat-ed aging program allowed us to estimate the motor in-service lifetime.

NH_(3)/CH_(4)/CH_(3)OH多孔介质燃烧特性模拟研究

氨(NH_(3))是一种无碳燃料,有望作为热能发电的替代燃料降低碳排放。多孔介质燃烧是一种可提高燃烧速率和稳定性的燃烧技术,实验表明其用于氨与反应性更强的燃料进行混燃可以同时提高燃烧强度和燃烧稳定性,但缺乏相应的模型研究。该文基于多孔介质导热强度高的特性,其内部燃烧满足一维假设,建立了一维多孔介质燃烧模型,对NH_(3)分别与甲烷(CH_(4))、甲醇(CH_(3)OH)掺混时的燃烧特性进行模型计算。计算结果显示多孔介质对两种混合燃料的作用不同,对于CH_(4)/NH_(3)燃料,多孔介质可以明显提高燃烧速率并降低富燃状态的NH_(3)残留;对于CH_(3)OH/NH_(3)燃料,提高燃烧速率和降低NH_(3)残留的效果较差;对两种混合燃料,可燃气体预混后直接送入多孔介质燃烧都增加一定的NOx排放,增加效果相同,而分级燃烧可以显著降低NOx排放。

两种换药方式对降低经烧伤创面置股静脉管感染率的效果观察

目的 探究不同换药方式对经烧伤创面置股静脉管感染率的效果,进一步探究经烧伤创面置股静脉管的换药规范和标准。方法 选取2022年3月—2023年2月本院收治的烧伤创面置股静脉管患者60例为研究对象,随机将患者分成观察组(30例)和对照组(30例)。其中,观察组使用规范换药方式,对照组使用常规换药方式。对两组的感染率实施对比。结果 观察组总感染率明显小于对照组,两组数据具备统计学意义(P<0.05)。观察组总满意率明显大于对照组,两组数据有统计学意义(P<0.05)。结论 规范换药方式可降低导管感染发生率,有效提高经烧伤创面股静脉置管期间患者护理质量,提升期间的安全性,增强患者对标准用药的满意度,值得临床推广。

超级铝热剂在固体推进剂中的应用研究进展

超级铝热剂具有高放热和高活性的特点,其反应速率和能量释放效率均显著高于传统铝热剂,应用于固体推进剂有望改善释能速率、效率、感度等指标,已成为固体推进剂的发展方向。总结了超级铝热剂的制备工艺、特点及其工业化应用潜力;论述了超级铝热剂在固体推进剂中的适用性;综述了超级铝热剂的微结构(燃料/氧化剂界面控制、核壳结构、多层膜结构)和组分(金属氧化物、氟材料、碳纳米材料)对固体推进剂燃烧性能和能量释放的影响。超级铝热剂的添加显著提高了热反应活性和放热量,增强了推进剂的点火及燃烧性能,同时存在工业生产成本高、工艺控制要求复杂、燃烧过程精密控制难度大等问题,展望了未来超级铝热剂在固体推进剂中应用的研究重点和发展方向。

降速剂及其作用位点对三组元推进剂燃烧性能的影响规律研究

针对两种典型季铵盐和金刚烷衍生物降速剂,研究了其作用位点对推进剂点火燃烧性能的影响。基于两种不同结构的Al@AP和AP@Al复合颗粒,将降速剂分布在不同作用位置:即AP颗粒内部和表面。利用扫描电子显微镜(SEM-EDS)和计算机断层扫描(CT)等技术对所制备复合颗粒微观形貌和结构进行表征,研究了降速剂对推进剂爆热、点火延迟和燃烧性能的影响。惰性降速剂的加入会使得推进剂爆热值降低,但Al@AP复合颗粒的高反应活性能部分抵消这一现象。与机械混合方式相比,当降速剂作用于AP表面时能明显延缓推进剂点火过程,其中金刚烷衍生物能使推进剂点火延迟时间增加至420 ms,比基础配方增加了192%。在基体中直接加入降速剂可以有效降低推进剂燃速,但其降压强指数效果有限。铝基复合颗粒和降速剂的共同作用能显著降低推进剂的高压燃速和压强指数:当作用位置在AP内时,两种降速剂使推进剂1~20 MPa内压强指数从基础配方的0.45分别降低至0.20和0.33,同时可使10~20 MPa压强指数分别减小了48%和49%。

石墨烯掺杂对B/KNO_(3)/PF激光点火特性的影响

为探索常压下石墨烯(Graphene)掺杂对B/KNO_(3)/PF点火和燃烧性能的影响,采用湿混法和冷冻干燥法分别制备了不同石墨烯掺杂量的Graphene/B/KNO_(3)/PF,并使用光电探测器和高速摄影研究了石墨烯掺杂量和装药密度对点火延迟时间和燃烧速度的影响规律。结果表明:相对于冷冻干燥法,湿混法制备的Graphene/B/KNO_(3)/PF混合均匀且燃烧速度更高。随着石墨烯掺杂量(0~2 wt%)的增加,Graphene/B/KNO_(3)/PF的平均燃烧速度先增大后减小。装药密度为1.5g·cm^(-3)时,0.8wt%石墨烯掺杂量的Graphene/B/KNO_(3)/PF燃烧速度最大(20.3 mm·s^(-1)),与B/KNO_(3)/PF(14.6 mm·s^(-1))相比增加了39.0%;在装药密度0.8~1.7 g·cm^(-3)范围(0.8 wt%石墨烯掺杂量)内,Graphene/B/KNO_(3)/PF药柱平均燃烧速度随着装药密度的增大而减小。

降速剂及其作用位点对丁羟四组元推进剂燃烧性能的影响规律

为研究降速剂对丁羟四组元推进剂燃烧性能的影响规律,将典型季铵盐和金刚烷衍生物两种高效降速剂引入核壳结构铝基复合颗粒Al@HMX和AP@Al,使其分别作用于HMX颗粒内部和AP颗粒表面,制备了4种含降速剂的铝基复合颗粒(Al/A@HMX,Al/B@HMX,AP@Al/A和AP@Al/B);采用扫描电子显微镜对样品形貌进行了表征;采用高速红外相机拍摄推进剂燃烧过程的火焰红外照片,并对推进剂的爆热、密度、点火延迟时间和燃速进行了测试。结果表明,加入惰性降速剂会导致推进剂爆热降低,而Al@HMX复合颗粒能部分抵消这一现象,使推进剂爆热值增加了338 J/g;降速剂能够抑制AP和HMX的热分解过程,使达到AlO辐射峰值前维持低强度的“平台段”;而引入Al@HMX后,推进剂的点火延迟时间比基础配方减小49.4%;在10~20 MPa范围内两种降速剂均能有效降低推进剂燃速,在此基础上采用Al@HMX可使含季铵盐丁羟四组元推进剂20 MPa下的燃速降低7.1 mm/s(38.4%),压强指数降至0.25;当降速剂作用于AP表面时,含质量分数1%季铵盐的推进剂在20 MPa下燃速可降低5.0 mm/s(27.3%)。

含能燃速抑制剂的制备及其对AP分解的负催化效应

燃速抑制剂作为固体推进剂的核心功能组分,在降低固体推进剂高压燃速方面起关键作用。精准设计具有降速效应的季铵与醛基结构,获得高氮三氨基胍乙二醛二维共聚物(Triaminoguaniding Glyoxal two dimensional Copolymer,TAGP)含能配体,并与碱土金属离子K^(+)、Ba^(2+)和Ca^(2+)发生络合反应,制备系列新型含能燃速抑制剂(TAGP-M)。采用粉末衍射、X射线光电子能谱、扫描电镜/能谱和差示扫描量热/热重联用等技术分析其形貌、结构和热稳定性,并研究这些含能燃速抑制剂对高氯酸铵(Ammonium Perchlorate,AP)热分解的负催化作用。研究结果表明:TAGP-K对AP转晶抑制最为显著,使AP的转晶吸热峰温提高5.9℃、低温分解峰峰温升高28.7℃;添加10 wt%的TAGP-K,可使AP的最大热分解速率降低58%;TAGP-Ca燃速抑制剂可使AP的释能效应集中在高温分解过程,AP/TAGP-Ca混合体系的放热量比纯AP提高50%以上;TAGP-Ca和TAGP-Ba燃速抑制剂在抑制含AP分解的同时提高了其释能效率;TAGP-M燃速抑制剂在分解过程中释放NH_(3)并与AP分解产物HClO_(4)结合,形成更难分解的M(ClO_(4)^(-))n;通过碱土离子与ClO_(4)^(-)离子强静电作用,抑制后者分解产生氧化性气氛,进而抑制AP高温放热反应过程。

不同粒径黑火药点火过程中与纤维素壳体材料的热相互作用

为了研究点火装置中纤维素外壳对不同粒径黑火药固相反应放热特性、反应气相产物、点火燃烧特性等方面的影响,制备系列黑火药/纤维素复合物样品,并采用扫描电子显微镜表征其微观结构和形貌。通过同步热分析仪和傅里叶变换红外光谱仪联用,研究纤维素对黑火药热反应性能的影响。用氧弹量热仪测量各样品的爆热,利用综合燃烧诊断系统(高速相机和高速红外热像仪)获得黑火药及其纤维素复合物燃速与火焰温度分布。研究结果表明:纤维素会降低黑火药放热量,当纤维素含量为33.33%时,两种黑火药的总放热量分别降低了66.4%和58.5%;纤维素并未改变黑火药热解路径;黑火药的主要气相产物分别为H_(2)O、CO_(2)和NO_(2),与纤维素复合后除浓度变化外,气相产物种类保持不变;纤维素仅影响黑火药能量释放过程,但对不同粒径黑火药的能量释放影响的差别较小,与纤维素复合后能量释放变化仅相差3.1%。实验研究发现,小粒径黑火药及其纤维素复合物燃烧更剧烈,火焰面积更大、燃温更高;纤维素对黑火药的燃烧起消极作用,主要是降低黑火药的燃速和火焰辐射强度,火焰温度分别降低273.7℃和299.4℃;黑火药及其纤维素复合物的凝聚相产物形貌表明纤维素一定程度上促进了黑火药凝相产物团聚,即纤维素会降低其燃烧效率。

一种面向丁羟推进剂燃速预测的机器学习融合模型

建立了以端羟基聚丁二烯(HTPB)推进剂原材料参数和组分含量为输入变量、燃速值为输出的机器学习预测模型。首先,通过经验性单因素规律对包括随机森林回归、支持向量回归、高斯过程回归、核岭回归和径向基函数模型等进行了初筛;然后,以最大绝对误差(AE_(max))、最大相对误差(RE_(max))、均方根误差(RMSE)及平均绝对误差(MAE)作为模型的性能评价指标,对不同模型的预测性能进行对比,筛选出最大相对误差RE_(max)<5%的模型,对通过筛选的模型进行融合获得最终的燃速预测模型,并将融合模型与单一模型的预测性能进行对比;最后,利用样本集外的10组数据对融合模型的预测精度进行了验证。结果表明,融合模型的RE_(max)和RMSE小于任何单一模型,其中AE_(max)=0.68、RE_(max)=3.97%、RMSE=0.3214、MAE=0.253,可实现对此类HTPB推进剂燃速的高精度、高效率预测。

基于超声的标准发动机动态燃速测试技术

以标准发动机的动态燃速测试技术为研究对象,应用超声测厚原理获取固定声速点火条件下的发动机动态燃速、压强数据;分析提出一种基于特征点的动态燃烧信号辨识方法,获取发动机点火过程中推进剂退移厚度与时间变化数据;通过试验的方法建立常温状态不同压强下的声速校准模型,结合测试过程压强数据计算得到发动机点火过程中超声的实时声速,代入前期在固定声速条件下获取的推进剂退移厚度与时间数据中,通过求导获取点火过程中发动机的实时燃速。计算结果表明:基于超声的动态燃速测试方法能够实现整机的动态燃速测试,具有较高的时间分辨精度,其中基于超声的动态燃速测试燃烧时间与传统压强-时间曲线计算得到的燃烧时间误差为0.235%。此外,对比发动机点火后压强-时间与动态燃速-时间曲线发现,发动机建压完成后的动态燃速与压强曲线变化趋势呈一定相似性。