Inventory models with nonlinear shortage costs and stochastic lead times; applications of shape properties of randomly stopped counting processes

In this article, we study generalizations of some of the inventory models with nonlinear costs considered by Rosling in (Oper. Res. 50 (2002) 797–809). In particular, we extend the study of both the periodic review and the compound renewal demand processes from a constant lead time to a random lead time. We find that the quasiconvexity properties of the cost function (and therefore the existence of optimal (s, S) policies), holds true when the lead time has suitable log‐concavity properties. The results are derived by structural properties of renewal delayed processes stopped at an independent random time and by the study of log‐concavity properties of compound distributions. © 2015 Wiley Periodicals, Inc. Naval Research Logistics 62: 345–356, 2015     

固冲补燃室团聚硼颗粒燃烧试验

研究团聚硼颗粒在补燃室中的点火燃烧对提高固冲发动机性能具有重要意义。通过试验模拟固冲发动机工作过程的方法,开展了补燃室流场条件下的团聚硼颗粒点火燃烧试验。结合高速火焰图像处理技术和流场参数测量结果,对试验中团聚硼颗粒的点火燃烧状态、火焰结构以及颗粒尺寸变化等进行了分析,获得了补燃室燃气温度和氧气含量等因素对团聚硼颗粒点火燃烧过程的影响机制。对燃烧残渣进行了分析,发现燃烧前后颗粒尺寸变化不大,燃烧过程中高温气流可能进入了颗粒内部并与硼颗粒发生反应。     

考虑不确定参数及外部扰动数字液压缸非线性鲁棒位置跟踪控制

在考虑不确定参数及外部扰动的情况下为数字液压缸位置跟踪系统设计了一个非线性控制器。首先,建立了数字液压缸位置跟踪系统的非线性模型;然后,构造了一个李雅普诺夫函数及非线性控制器,推导了系统鲁棒稳定的充分条件,由此将非线性控制器的设计问题转化成为线性矩阵不等式的求解问题;最后,进行了仿真及实验验证。结果表明:所设计的控制器对于参数不确定性及外部扰动具有良好的鲁棒稳定性及更好的动态特性。     

基于主成分分析的储运过程管道堵塞故障检测

针对现代储运过程典型的管道堵塞故障,分析了其对过程监控参数的影响;采用基于主成分分析的故障检测方法,构建了故障检测流程和检测模型;以储运过程典型仿真系统为研究对象,建立了主成分模型;通过模拟不同程度的管道堵塞故障,进行了管道堵塞故障检测的仿真应用研究,获得了管道堵塞故障统计量控制图.实验结果表明了基于主成分分析的故障检测方法的有效性和正确性.     

变距离静电电位检测研究

针对现有非接触式静电检测装置存在检测距离近且距离固定等问题,提出了对电位测量进行距离补偿的变距离静电电位检测方案。首先,从电位测量的基本原理出发,分析了距离测量误差与电位测量误差的关系,验证了精确测距的重要性,即要满足电位测量相对误差σV≤±10%,所选测距方式的距离测量相对误差-4.65%≤σd0≤5.41%的技术指标。然后,通过实验研究了检测距离与感应电位的关系,验证了0.5 m内对静电电位变距离测量的可行性,得到了对电位测量进行距离补偿的公式雏形Vs(V a,d)=Va(a+bd)c。依据此公式雏形以及大量的重复实验,可以得到公式中的各项参数值,编入单片机可实现对静电电位的变距离检测。     

火力作战目标决策分析

为满足火力作战多样化的任务需求,结合对火力作战行动有效作用空间的具体解析,对其目标决策进行了深入的分析,在把握时代特征的同时,较为系统地总结出火力作战目标决策的新要求、新方法和新流程,为信息化条件下组织筹划火力作战提供建设性理论参考。     

Two novel critical shock models based on Markov renewal processes

In this paper, we investigate systems subject to random shocks that are classified into critical and noncritical categories, and develop two novel critical shock models. Classical extreme shock models and run shock models are special cases of our developed models. The system fails when the total number of critical shocks reaches a predetermined threshold, or when the system stays in an environment that induces critical shocks for a preset threshold time, corresponding to failure mechanisms of the developed two critical shock models respectively. Markov renewal processes are employed to capture the magnitude and interarrival time dependency of environment-induced shocks. Explicit formulas for systems under the two critical shock models are derived, including the reliability function, the mean time to failure and so on. Furthermore, the two critical shock models are extended to the random threshold case and the integrated case where formulas of the reliability indexes of the systems are provided. Finally, a case study of a lithium-ion battery system is conducted to illustrate the proposed models and the obtained results.     

无人机飞行训练资源配置效率的AHP-Arena综合评价方法

为降低传统层次分析法(analytic hierarchy process,AHP)赋权过程主观片面性影响,提出了一种综合AHP与Arena仿真建模技术的无人机训练资源配置效率评价方法。基于飞行训练流程分析,确定了训练资源配置效率影响因素和效率评价指标,建立了层次型综合评价体系,概括了AHP-Arena综合评价步骤。利用Arena建模软件构建训练流程动态仿真系统并验证有效性,采用单变量数值仿真法、均方差决策法完成了影响因素客观赋权,通过线性加权综合法得出综合评价系数,实现资源配置效率评价与方案优选。实例应用说明了该方法的有效性,同时,该方法可推广至其他类似的训练过程中,亦可为其他多因素、多指标评价决策过程提供借鉴。     

Burning characteristics of high density foamed GAP/CL-20 propellants

The monolithic foamed propellants with high densities were prepared by casting and two-step foaming processes. Glycidyl azide polymer (GAP) and isocyanate were used as the binder system and 2,4,6,8,10,12-hexanitro-2,4,6,8,10,12-hexaazaisowurtzitane (HNIW, CL-20) was employed as the energetic component. The newly designed formulation containing 60 % CL-20 produced a force constant of 1077 J/g and low flame temperature of 2817 K. Two foamed propellants with densities of 1.32 g/cm³ and 1.53 g/cm³ were fabricated by a confined foaming process and examined by closed bomb tests. The results revealed that porosity significantly affects burning performance. A size effect on combustion behaviors was observed for the foamed propellant with 5.56 % porosity, and a double-hump progressive dynamic vivacity curve was obtained. At last, the 30 mm gun test was carried out to demonstrate the interior ballistic performance, and the muzzle velocity increased by 120 m/s at the same maximum chamber pressure when monolithic propellant was added in the charge.     

Controllable combustion behaviors of the laser-controlled solid propellant

Microsatellites have been widely applied in the fields of communication,remote sensing,navigation and science exploration due to its characteristics of low cost,flexible launch mode and short development period.However,conventional solid-propellant have difficulties in starting and interrupting combustion because combustion is autonomously sustained after ignition.Herein,we proposed a new type of solid-propellant named laser-controlled solid propellant,which is sensitive to laser irradiation and can be started or interrupted by switching on/off the continuous wave laser.To demonstrate the feasibility and investigate the controllable combustion behaviors under different laser on/off conditions,the combus-tion parameters including burning rate,ignition delay time and platform pressure were tested using pressure sensor,high-speed camera and thermographic camera.The results showed that the increase of laser-on or laser-off duration both will lead to the decrease of propellant combustion performance during re-ignition and re-combustion process.This is mainly attributed to the laser attenuation caused by the accumulation of combustion residue and the change of chamber ambient temperature.Simultaneously,the multiple ignition tests revealed that the increased chamber ambient temperature after combustion can make up for the energy loss of laser attenuation and expansion of chamber cavity.However,the laser-controlled combustion performance of solid propellant displayed a decrease trend with the addi-tion of ignition times.Nevertheless,the results still exhibited good laser-controlled agility of laser-controlled solid propellant and manifested its inspiring potential in many aspects of space missions.