基于紧支径向基函数的固体域耦合数据传递方法

针对热-电场耦合仿真计算中非匹配网格之间的数据插值问题,提出了一种基于紧支径向基函数点插值的数据传递方法。推导了数据传递矩阵,根据所提出的数据传递方法编制了非匹配网格之间数据传递计算程序,以若干组非匹配网格之间的温度插值为例对本文所提方法进行了验证,并分析了不同参数对计算时间及精度的影响,结果表明,本文算法效率较高,计算误差较小,适用于以热-电场耦合为代表的固体域耦合非匹配网格间的数据传递计算。     

Recent advances in catalytic combustion of AP-based composite solid propellants

Composite solid propellants (CSPs) have widely been used as main energy source for propelling the rockets in both space and military applications. Internal ballistic parameters of rockets like characteristic exhaust velocity, specific impulse, thrust, burning rate etc., are measured to assess and control the performance of rocket motors. The burn rate of solid propellants has been considered as most vital parameter for design of solid rocket motors to meet specific mission requirements. The burning rate of solid propellants can be tailored by using different constituents, extent of oxidizer loading and its particle size and more commonly by incorporating suitable combustion catalysts. Various metal oxides (MOs), complexes, metal powders and metal alloys have shown positive catalytic behaviour during the com-bustion of CSPs. These are usually solid-state catalysts that play multiple roles in combustion of CSPs such as reduction in activation energy, enhancement of rate of reaction, modification of sequences in reaction-phase, influence on condensed-phase combustion and participation in combustion process in gas-phase reactions. The application of nanoscale catalysts in CSPs has increased considerably in recent past due to their superior catalytic properties as compared to their bulk-sized counterparts. A large surface-to-volume ratio and quantum size effect of nanocatalysts are considered to be plausible reasons for improving the combustion characteristics of propellants. Several efforts have been made to produce nanoscale combustion catalysts for advanced propellant formulations to improve their energetics. The work done so far is largely scattered. In this review, an effort has been made to introduce various combustion catalysts having at least a metallic entity. Recent developments of nanoscale combustion catalysts with their specific merits are discussed. The combustion chemistry of a typical CSP is briefly discussed for providing a better understanding on role of combustion catalysts in burning rate enhancement. Available information on different types of combustion nanocatalysts is also presented with critical comments.     

几种易燃液体燃烧烟尘微观形貌特征研究

利用透射电子显微镜对几种易燃液体燃烧烟尘的微观形貌进行了研究,发现微观上易燃液体燃烧烟尘为分散的凝团,凝团形态为链状、簇状和絮状,在高倍率下观察发现,凝团是由直径几十纳米的准球形基本组成颗粒互相链接而成的。采烟高度和时间对烟尘形貌特征的辨别没有产生显著影响。     

基于缸盖振动的燃油喷射系统故障诊断

对V型12缸柴油机缸盖振动燃烧段信号与缸内压力进行了时域对比,分析了失火时的缸盖振动响应,研究了供油规律随转速变化情况。分析表明缸盖振动中包含喷油器针阀落座的振动响应,研究了基于短时能量动态双阈值端点检测提取针阀落座响应时间特征的方法,利用振动信号的峰值加速度来表征针阀落座的强度。在不同工况及不同状态下提取了针阀落座时间及强度的振动特征,结果表明：振动特征能够有效反映针阀的工作情况,可以用于燃油喷射系统故障的诊断。     

纵向涡发生器对棒状燃料元件温度场的影响分析

运用CFD方法,模拟计算了在反应堆棒状燃料元件包壳表面加装纵向涡产生器(LVG)后,燃料棒、气隙、包壳和冷却剂的温度场和冷却剂的流场。计算时采用分块结构网格对带LVG的计算区域划分网格,使用SSTk-ω模型模拟冷却剂的湍流流动,对于控制方程和湍流方程的离散采用二阶格式以保证计算精度。计算结果表明:加装LVG后,包壳和冷却剂间的换热有所改善,燃料棒、气隙和包壳的最高温度有所降低。在LVG附近,燃料棒、气隙、包壳和冷却剂温度均会出现一个峰值,然后急剧下降。冷却剂流动的湍动能突然增强,有效地增强了冷却剂的横向流动,经过LVG后,湍动能逐渐减弱,横向流动速度也逐渐减小。     

载机军舰航空燃油分段接力式补给模型

为解决载机军舰远洋作战时所需的航空燃油按时补给问题,建立了带有自动调节系统的载机军舰航空燃油分段接力式补给的预测模型。对航空燃油分段接力式补给进行研究,采用系统动力学方法,构建影响补给船队补给效率的各元素因果回路图与存量流量图及预测模型,并以系统动力学软件Vensim PLE 5.9为平台进行建模仿真。运行结果表明,该模型在扰动条件下能进行航空燃油分段接力式补给趋势的预测,可为航空燃油分段接力式补给方案的制定提供理论依据。     

Novel aluminum-based fuel: Facile preparation to improve thermal reactions

To improve the thermal properties of aluminum (Al) in the energetic system, a coated structure with ammonium perchlorate (AP) was prepared by a facile approach. And N, N-Dimethylformamide (DMF) was chosen as an ideal solvent based on heterogeneous nucleation theory and molecular dynamics simulation. This coated structure could enlarge the contact area and improve the reaction environment to enhance the thermal properties. The addition of AP could accelerate oxidation temperature of Al with around 17.5 °C. And the heat release of 85@15 composition rises to 26.13 kJ/g and the reaction degree is 97.6% with higher peak pressure (254.6 kPa) and rise rate (1.397 MPa/s). An ideal ratio with 15 wt% AP was probed primarily. The high energy laser-induced shockwave experiment was utilized to simulate the reaction behavior in hot field. And the larger activated mixture of coated powder could release more energy to promote the growth of shockwave with higher speed up to 518.7 ± 55.9 m/s. In conclusion, 85@15 composition is expected to be applied in energetic system as a novel metal fuel.     

FAE野外空中爆炸效应实验研究及其一次起爆机理探讨

野外进行1．8kg的FAE静爆实验,采用不同配方的纯固态燃料和液一固混合燃料与等质量的TNT对比分析。实验结果表明,FAE的爆炸效果明显优于等质量的TNT,而纯固态FAE爆炸性能强于液一固混合FAE;FAE爆炸后测到的超压分布呈现单调减趋势,这是由于测量点都分布在云爆区范围之外;FAE的云雾分散效果优于等质量的TNT装药,火焰持续时间也长。通过高速摄影图片看出,合适配方的纯固态无约束的FAE弹体火球的持续时间与有约束的液一固混合FAE弹体相当。分析了纯固态FAE爆炸后超压峰值时刻与火球最大直径时刻不同步的原因,探讨了纯固态FAE一次起爆机理。     

参数法估算船用增压锅炉试验时的燃油耗量

针对船用增压锅炉的运用 ,在分析比较传统方法的不足之后 ,推出了用参数法估算船用增压锅炉试验时的燃油耗量的方法 .     

柴油机燃油供给系统故障模糊诊断研究

通过分析柴油机燃油供给系统的故障表现形式及高压油管的油压波形特征 ,研究了柴油机燃油供给系统的故障诊断策略。首先 ,利用转速波动的扭矩谐波比诊断燃油供给系统是否有故障 ,再利用最大加速因子进一步确定故障源 ,最后 ,从高压油管的油压波形中提取诊断特征参数 ,用多参数模糊诊断的方法来诊断燃油供给系统的常见故障 ,并将此方法应用于柴油机故障诊断专家系统中 ,取得了满意的效果