激励器结构参数对合成射流影响的试验研究

为了设计高性能的合成射流激励器,实验采用热线风速仪测量激励器出口的流动速度,对不同大小激励器、不同出口形状激励器、单 双膜激励器以及金属振动膜处于不同装配受压状态下的激励器分别进行了试验。实验结果显示:激励器的结构决定了合成射流激励器的性能;激励器出口射流平均速度除了与激励器大小、出口面积有关外,还与出口形状有关,采用方孔 矩形孔形式的开口有利于建立较强的合成射流;双膜与单膜工作相比,合成射流最大速度基本上是成两倍关系;金属振动膜的安装形式(受压状态)不影响合成射流随频率的变化规律,但对合成射流速度影响很大,当激励器振动膜处于螺栓拧紧受压状态时,与振动膜不受压状态相比,合成射流出口速度几乎下降了一个数量级。     

数组越界软件测试系统的设计与实现

软件测试系统的研制是现阶段软件测试领域研究的一个热点.首先针对C/C 语言常见数组越界错误类型进行了分析,介绍了软件测试的一些基本概念,而后给出了软件测试系统设计,对系统设计的各个阶段进行了说明,并且给出了一种错误类型检查的算法设计,它在软件测试检测中具有通用性和代表性,最后给出了软件测试的实验结果.     

An efficient metaheuristic for integrated scheduling and staffing IT projects based on a generalized minimum cost flow network

Scheduling IT projects and assigning the project work to human resources are an important and common tasks in almost any IT service company. It is particularly complex because human resources usually have multiple skills. Up to now only little work has considered IT‐specific properties of the project structure and human resources. In this article, we present an optimization model that simultaneously schedules the activities of multiple IT projects with serial network structures and assigns the project work to multiskilled internal and external human resources with different efficiencies. The goal is to minimize costs. We introduce a metaheuristic that decomposes the problem into a binary scheduling problem and a continuous staffing problem where the latter is solved efficiently by exploiting its underlying network structure. For comparison, we solve the mixed–binary linear program with a state–of–the–art commercial solver. The impacts of problem parameters on computation time and solution gaps between the metaheuristic and the solver are assessed in an experimental study. Our results show that the metaheuristic provides very favorable results in considerable less time than the solver for midsize problems. For larger problems, it shows a similar performance while the solver fails to return feasible solutions. © 2012 Wiley Periodicals, Inc. Naval Research Logistics 59: 111–127, 2012     

k-ary n-cube中的移动气泡流控策略

在k-ary n-cube网络中,气泡流控是一种有效、实用的死锁避免技术,它不必依赖虚通道就能避免环网中出现的死锁问题。如果流控策略能感知到维度内缓冲区的总体使用情况,就能够更加高效地进行调度,从而提高网络性能。为了避免关键气泡机制引起的阻塞,提出了伪报文协议;结合伪报文协议,设计了移动气泡流控策略,它有效实现了维度内的全局资源感知能力。与局部气泡流控相比,路由器每条输入通道仅设置一个报文缓冲区就可以避免环网中的死锁,即最小资源需求减少了一半。网络模拟结果表明,该机制不会出现永久阻塞;在distribute、hotregion和uniform传输模式中,该机制可以有效提高网络吞吐率20%以上,并且在网络饱和后吞吐率依然维持稳定。     

一类有增益网络的最大流模型

一般带容量限制的网络图中流出源点与流入汇点的流量相等,但在实际应用中,存在一类流量经过弧发生变化的网络,使得流出源点与流入汇点的流量不相等。针对此类问题,建立了增益网络最大流模型,并通过增设虚弧将增益网络转换成循环网络,利用循环网络中汇点流量瞬间平衡的优点简化了模型。最后,结合实例进行分析,编写程序对实例进行了计算,计算结果验证了该模型的有效性。     

油-水旋流器流场数值模拟研究

采用改进后的双方程湍流模型和SIMPLE计算方法,对切流式单入口油-水旋流器内部流场进行了模拟研究。结果表明:旋流器内部三维流场各向异性,即同一位置流体在不同方向的流动参数变化很大,流体质点在不同条件下的运动轨迹、速度、分离特性等方面都有较大差别;圆柱段与圆锥段的流场在柱锥结合面发生变化,旋流器的主要分离过程在圆锥段完成;单入口旋流器的流场中心与几何中心有偏差,对流场的稳定和分离会产生影响。该模拟结果与他人所做实验结果比较接近,说明该模型和算法是可靠的,为旋流器的实际应用提供了参考。     

进气口位置和进气体积流量对油罐油气惰化置换效率的影响

采用机械通风方式对油罐油气进行处理,具有安全性差、通风时间长和效率低下的缺点;利用燃惰气对油罐油气进行处理,可较好地克服上述缺点。在前期研究的基础上,设计模拟实验台架,以燃惰气为介质,实验研究进气口位置和进气体积流量对燃惰气惰化置换油罐油气的影响。     

基于任务的连续出动舰载机航空保障重调度研究

对舰载机和各种保障资源进行调度是提高舰载机航空保障效率、保证舰载机所承担作战任务顺利完成的有效手段。为了克服以往研究中没有考虑作战任务变更对舰载机航空保障调度的影响,使用重调度的理论与方法研究了基于任务的连续出动舰载机航空保障重调度问题,建立了连续出动舰载机航空保障重调度模型。采用免疫算法对模型进行求解,可以避免模型的解空间可能出现组合爆炸问题。最后通过一个实例表明该模型可以很好的应对由作战任务变更所引起的重调度问起,算法求解速度满足作战需求,从而验证了模型的准确性及算法的有效性。     

Numerical studies on four-engine rocket exhaust plume impinging on flame deflectors with afterburning

This paper studies the four-engine liquid rocket flow field during the launching phase. Using three-dimensional compressible Navier-Stokes equations and two-equation realizable k-epsilon turbulence model, an impact model is established and flow fields of plume impinging on the two different shapes of flame deflectors, including wedge-shaped flame deflector and cone-shaped flame deflector, are calcu-lated. The finite-rate chemical kinetics is used to track chemical reactions. The simulation results show that afterburning mainly occurs in the mixed layer. And the region of peak pressure occurs directly under the rocket nozzle, which is the result of the direct impact of exhaust plume. Compared with the wedge-shaped flame deflector, the cone-shaped flame deflector has great performance on guiding exhaust gas. The wedge-shaped and cone-shaped flame deflectors guide the supersonic exhaust plume away from the impingement point with two directions and circumferential direction, respectively. The maximum pressure and temperature on the wedge-shaped flame deflector surface are 37.2% and 9.9% higher than those for the cone-shaped flame deflector. The results provide engineering guidance and theoretical significance for design in flame deflector of the launch platforms.     

Numerical research on adverse effect of muzzle flow formed by muzzle brake considering secondary combustion

The simulation of the artillery interior and intermediate ballistics problem is performed to investigate the influence of a gas dynamics device, muzzle brake, on the muzzle hazard phenomena, such as flash and blast waves. The correlation of the chemical reactions with the characteristics of the muzzle flow field is analyzed by the simulation for a further understanding of the secondary combustion phenom-enon of the muzzle flow. The novel structure of muzzle flow caused by the muzzle brake is presented by the simultaneous solution of the interior ballistics model and multi-species Navier-Stokes equations in order to analyze the influence of the muzzle brake structure on the chemical reactions. The secondary combustion of the muzzle flow due to the oxygen-supplement chemical reactions is obtained by the chemical reaction kinetic model. The interaction of the blast waves released from the muzzle brake is illustrated in detail and the mechanism of the formation of muzzle flash is analyzed. This research provides a reference for the studies on the suppression of the muzzle flash.