攻角对双三角翼旋涡特性影响的数值模拟

采用数值方法研究了双三角翼上涡流运动随攻角的变化规律.计算取层流假设,研究了攻角在5°～30°,76°/40°后掠双三角翼绕流的流场结构随攻角的变化,并对双三角翼上涡破裂现象对流场结构及气动力性能的影响进行了分析.结果表明,双三角翼上的多涡结构存在强烈的相互影响,较大的攻角会导致涡破裂在翼面上发生,严重影响了双三角翼的气动力性能.     

带控制舵机动弹头粘性绕流数值模拟

采用空间二阶精度的交替方向隐式分解的NND格式求解完全气体假定下的非定常薄层近似Navier Stokes方程 ,并采用抛物化的椭圆型方程生成复杂带翼外形的空间网格。最后给出带控制舵机动弹头在M∞ =7 3,α =2 0°下所计算的流场等值线、表面压强分布及表面极限流线     

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.     

靴形喷油速率耦合预喷射对超高压共轨柴油机性能的影响

在介绍超高压共轨系统工作原理的基础上,基于GT-Power软件建立单缸超高压共轨柴油机的仿真模型,并利用试验验证模型的准确性,而后通过模型分析不同喷油速率、靴形喷油速率耦合不同预喷油量和靴形喷油速率耦合不同预喷提前角对超高压共轨柴油机动力性、经济性以及燃烧排放特性的影响。结果表明:通过调整超高压共轨系统中电控增压器电磁阀和喷油器电磁阀的开启时间,能够实现喷油速率的柔性可调。随着喷油速率从矩形变化到靴形,柴油机缸内压力、温度以及NO_x排放量均逐渐降低,而soot排放量逐渐升高,且靴形喷油速率可使柴油机获得最大的功率(扭矩)和最低的油耗率。靴形喷油速率耦合较小的预喷油量可以使柴油机获得更好的动力性、经济性和燃烧特性,但同时也会导致NO_x排放量的升高。靴形喷油速率耦合较大的预喷提前角有助于改善柴油机排放特性,但受到预喷油量的限制,效果并不明显。     

A general model of heterogeneous system lifetimes and conditions for system burn‐in

Burn‐in is a technique to enhance reliability by eliminating weak items from a population of items having heterogeneous lifetimes. System burn‐in can improve system reliability, but the conditions for system burn‐in to be performed after component burn‐in remain a little understood mathematical challenge. To derive such conditions, we first introduce a general model of heterogeneous system lifetimes, in which the component burn‐in information and assembly problems are related to the prediction of system burn‐in. Many existing system burn‐in models become special cases and two important results are identified. First, heterogeneous system lifetimes can be understood naturally as a consequence of heterogeneous component lifetimes and heterogeneous assembly quality. Second, system burn‐in is effective if assembly quality variation in the components and connections which are arranged in series is greater than a threshold, where the threshold depends on the system structure and component failure rates. © 2003 Wiley Periodicals, Inc. Naval Research Logistics 50: 364–380, 2003.     

切向空气气流对激光辐照碳纤维复合材料的影响

实验研究了靶材表面存在和不存在切向空气气流时,975nm连续激光对碳纤维增强树脂基复合材料的辐照效应,发现切向气流的加载有利于激光对碳纤维复合材料的破坏.从理论上对激光辐照下碳纤维复合材料的破坏机理进行了初步分析,基于碳的氧化特性和氧化反应机理,推导了碳纤维的氧化速率方程.采用改进的光滑粒子方法,对激光辐照下复合材料树...     

如何估计软件的MTBF

软件剩余初始故障个数No、平均无故障时间MTBF、故障暴露率λ和软件运行的成功率θ等是衡量软件可靠性的重要参数.其中对高可靠性软件(包括军用软件等)MTBF是最重要的.传统的MTBF计算方法有2种一是计算发生故障的平均时间间隔二是通过软件可靠性模型进行估计.前者代价较大,后者不太准确.本文从软件的失败率入手研究软件的MTBF,这是一个比较贴近实际的方法.     

后方油库整体生存概率分析计算

针对我军后方油库特点,探讨了油库整体生存概率计算的基本思路和方法,分析了各类分项目标生存概率的计算方法,采用层次分析对后方油库各分项目标权值进行了详细分析计算,可为后方油库伪装防护效能评估提供依据。     

数值模拟类升力体外形高超声速粘性绕流

采用空间二阶精度的交替方向隐式分解的NND格式求解完全气体假定下的非定常薄层近似Navier Stokes方程 ,并采用抛物化的椭圆型方程生成复杂带翼外形的空间网格。最后给出了类升力体外形在M∞ =8 0 ,α =2 0°下的流场计算结果。     

Optimal (τ, T) opportunistic maintenance of a k‐out‐of‐n:G system with imperfect PM and partial failure

The opportunistic maintenance of a k‐out‐of‐n:G system with imperfect preventive maintenance (PM) is studied in this paper, where partial failure is allowed. In many applications, the optimal maintenance actions for one component often depend on the states of the other components and system reliability requirements. Two new (τ, T) opportunistic maintenance models with the consideration of reliability requirements are proposed. In these two models, only minimal repairs are performed on failed components before time τ and the corrective maintenance (CM) of all failed components are combined with PM of all functioning but deteriorated components after τ; if the system survives to time T without perfect maintenance, it will be subject to PM at time T. Considering maintenance time, asymptotic system cost rate and availability are derived. The results obtained generalize and unify some previous research in this area. Application to aircraft engine maintenance is presented. © 2000 John Wiley & Sons;, Inc. Naval Research Logistics 47: 223–239, 2000