SiCw/Al复合材料的强度分析

用简化应力的分析方法推导了SiCw Al复合材料的强度与SiC晶须偏轴角α的关系,并通过试验进行验证.结果表明,计算的SiCw Al复合材料强度与实测值比较接近,其误差归因于压缩变形过程中SiC晶须发生了转动和折断,改变了SiC晶须的偏轴角和平均长径比.     

Experimental investigation on enhanced damage to fuel tanks by reactive projectiles impact

Enhanced damage to the full-filled fuel tank,impacted by the cold pressed and sintered PTFE/AL/W reactive material projectile(RMP)with a density of 7.8 g/cm3,is investigated experimentally and theoretically.The fuel tank is a rectangular structure,welded by six pieces of 2024 aluminum plate with a thickness of 6 mm,and filled with RP-3 aviation kerosene.Experimental results show that the kerosene is ignited by the RMP impact at a velocity above 1062 m/s,and a novel interior ignition phenomenon which is closely related to the rupture effect of the fuel tank is observed.However,the traditional steel projectile with the same mass and dimension requires a velocity up to 1649 m/s to ignite the kerosene.Based on the experimental results,the radial pressure field is considered to be the main reason for the shear failure of weld.For mechanism considerations,the chemical energy released by the RMP enhances the hydrodynamic ram(HRAM)effect and provides additional ignition sources inside the fuel tank,thereby enhancing both rupture and ignition effects.Moreover,to further understand the enhanced ignition effect of RMP,the reactive debris temperature inside the kerosene is analyzed theoretically.The initiated reactive debris with high temperature provides effective interior ignition sources to ignite the kerosene,resulting in the enhanced ignition of the kerosene.     

Influence of propagation direction on operation performance of rotating detonation combustor with turbine guide vane

Due to the pressure gain combustion characteristics, the rotating detonation combustor (RDC) can enhance thermodynamic cycle efficiency. Therefore, the performance of gas-turbine engine can be further improved with this combustion technology. In the present study, the RDC operation performance with a turbine guide vane (TGV) is experimentally investigated. Hydrogen and air are used as propellants while hydrogen and air mass flow rate are about 16.1 g/s and 500 g/s and the equivalence ratio is about 1.0. A pre-detonator is used to ignite the mixture. High-frequency dynamic pressure transducers and silicon pressure sensors are employed to measure pressure oscillations and static pressure in the combustion chamber. The experimental results show that the steady propagation of rotating detonation wave (RDW) is observed in the combustion chamber and the mean propagation velocity is above 1650 m/s, reaching over 84% of theoretical Chapman-Jouguet detonation velocity. Clockwise and counterclockwise propagation directions of RDW are obtained. For clockwise propagation direction, the static pressure is about 15% higher in the combustor compared with counterclockwise propagation direction, but the RDW dominant frequency is lower. When the oblique shock wave propagates across the TGV, the pressure oscillations reduces significantly. In addition, as the detonation products flow through the TGV, the static pressure drops up to 32% and 43% for clockwise and counterclockwise propagation process respectively.     

P3，4m的优美性

设u、v是两个固定顶点,用b条内部互不相交且长度均为a的道路连接u、v所得到的图用Pa,b表示.Kathiresan证实P2r,2m-1(r,m均为任意正整数)是优美的,且猜想除了(a,b)=(2r+1,4s+2)外,所有的Pa,b都是优美的.杨元生已证实P2r+1,2m-1是优美的.本文证明P3,4m是优美图,从而当a=3时Kathiresan猜想成立.     

一个输入依赖于系统状态的排队模型的瞬时队长分布

探讨了一个有如下特征的排队系统:该系统的第m个到达间隔αm-αm-1(m≥1)的分布依赖系统在时刻αm-1拥有的顾客数目。应用补充变量方法,这个系统的瞬时队长分布的积分表示被得到。在各到达间隔分布和诸服务时间分布均具有密度函数的条件下,这个积分表示的被积项能够递归地求取。     

适于卫星闪电监测系统的地面站数目配置初探

闪电监测载荷搭载在不同卫星平台时,地面站对它的观测时间都会发生相应的改变,文中对其进行了计算,并对不同轨道高度下所需的地面站个数作了简要分析。     

基于信息系统的作战指挥效能“嵌入式”评估策略

在分析基于信息系统的作战指挥效能评估特点的基础上,提出了"嵌入式"作战指挥效能评估策略;按照指挥实体、指挥活动、指挥效果3个层次,梳理了指挥主体效能、指挥信息系统效能、指挥活动效能和指挥对象任务效能4个方面的评估内容框架;根据评估活动与作战指挥活动"一体化"原理,设计了作战指挥效能评估在各个作战阶段的活动流程,并进一步提出了作战指挥效能评估工具"功能性嵌入"作战指挥信息系统的方法。     

考虑相位噪声影响的单阵元被动合成阵列算法

考虑到现有单阵元被动合成阵列算法对阵元的运动模型假设过于理想且对相位噪声的适应能力不足,首先,提出一种适用于阵元任意机动方式的单阵元被动合成阵列通用算法,进而通过相位噪声模型分析,给出最大相参时间及有效合成阵元数的选取方法,重建了合成阵列的流形矢量,得到了与相位噪声模型相匹配的改进算法.然后,在相位噪声影响条件下,推导了单阵元被动合成阵列波达方向的理论估计方差下限.仿真分析表明,较未考虑相位噪声影响的算法,改进算法能够有效提高相位噪声影响下的单阵元被动合成阵列测向精度.     

航天器推进系统模块化建模方法

为了研究由复杂增压气路和推进剂供应管路组成的航天器推进系统的动力学问题,基于AMESim软件平台,构建了模块化、可扩展的航天器推进系统仿真模型UPSSim.模型中,增压气路采用分段集中参数模型,推进剂供应管路采用分布参数模型,并考虑了系统各组件与环境的换热.对某型轨控发动机的变轨过程进行了仿真,UPSSim能准确模拟该发动机变轨过程中系统参数的变化,计算结果与设计性能参数、飞行遥测数据吻合较好.仿真结果表明,本文所采用的模块化建模与仿真方法适用于复杂管网的建模,在航天器推进系统仿真建模与仿真领域具有较好的应用前景.     

火力分配环协同度的编队反导决策优化

舰艇编队协同反导决策是一个多阶段多目标的决策系统,依据模糊权距离和隶属度概念,考虑系统中各阶段的协同关系,提出基于火力分配环协同度的概念,将模糊优选理论与动态规划原理有机地结合起来,寻求基于舰艇编队协同反导的多阶段多目标优化的最优均衡策略,并应用于解决舰艇编队协同反导决策的优化中,得出了具有指导意义的结论。