5G与WiMAX双模AeroMACS机载终端设计与实现

针对现有航空移动机场通信系统(Aeronautical Mobile Airport Communication System,AeroMACS)尚未形成成熟的机载装机产品的问题,开展AeroMACS机载终端的研究。提出一种基于5G与WiMAX技术的双模AeroMACS机载终端设计方案,不仅能够实现国际标准WiMAX模式下的AeroMACS数据通信,而且利用国内5G技术的优势,大幅提升了AeroMACS机载终端的数据传输性能。通过设计的双通测试与传输速率测试方案,采用灌包测试的方法,验证了所设计的AeroMACS机载终端可以进行双模同时通信的功能,也表明了5G技术下的AeroMACS机载终端传输速率优于WiMAX技术。     

放射性气载流出物取样代表性分析

为获取核设施放射性气载流出物单点连续监测取样位置,提出基于随机轨道模型(DRW)的气-固多相湍流耦合方法求解代表性取样区域。借助k-epsilon湍流模型模拟连续相,并引入离散颗粒模型(DPM)模拟离散相,建立基于DRW模型的排风管道内流道气-固多相湍流耦合计算模型,计算了核设施气载流出物在管道内流道流场分布规律,分析了内流道流体气旋角、气流速度、示踪气体浓度、气溶胶粒子浓度与管道高度间的关联关系。分析结果表明,随着截面高度的增加,气旋角、气流速度变异系数(COV)、示踪气体浓度COV及示踪气体浓度最大值与平均值的偏差逐渐降低并趋于稳定,气溶胶粒子浓度COV在截面6与截面8满足取样代表性要求;基于计算流体动力学方法可快速地确定出代表性取样位置,为气载流出物单点取样现场试验提供了理论参考依据。     

基于双态混沌PSO的机载激光通信视轴稳定控制

机载空间激光通信视轴稳定是激光通信链路建立的前提。在视轴稳定平台中应用自抗扰控制方法取得了良好的控制效果,但自抗扰控制需调整参数众多且缺乏规范的调整手段。针对自抗扰控制调参难的问题,本文提出了一种利用双态混沌粒子群算法优化自抗扰控制参数的方法。仿真结果表明,与PSO-PID控制方法相比,该方法具有更快的响应速度,更强的抗干扰能力和更好的鲁棒性。     

Airborne spread of expiratory droplet nuclei between the occupants of indoor environments: A review

This article reviews past studies of airborne transmission between occupants in indoor environments, focusing on the spread of expiratory droplet nuclei from mouth/nose to mouth/nose for non‐specific diseases. Special attention is paid to summarizing what is known about the influential factors, the inappropriate simplifications of the thermofluid boundary conditions of thermal manikins, the challenges facing the available experimental techniques, and the limitations of available evaluation methods. Secondary issues are highlighted, and some new ways to improve our understanding of airborne transmission indoors are provided. The characteristics of airborne spread of expiratory droplet nuclei between occupants, which are influenced correlatively by both environmental and personal factors, were widely revealed under steady‐state conditions. Owing to the different boundary conditions used, some inconsistent findings on specific influential factors have been published. The available instrumentation was too slow to provide accurate concentration profiles for time‐dependent evaluations of events with obvious time characteristics, while computational fluid dynamics (CFD) studies were mainly performed in the framework of inherently steady Reynolds‐averaged Navier‐Stokes modeling. Future research needs in 3 areas are identified: the importance of the direction of indoor airflow patterns, the dynamics of airborne transmission, and the application of CFD simulations.     

煤矿采煤机控制系统设计研究

为了减少综放面工作人员劳动强度、增加采出率,研究了煤矿采煤机控制系统,分析了煤矿采煤机基本结构,主要包括电气系统、牵引传动部件、截割部件和其他辅助装置,提出了采煤机控制方案和流程,系统主要包括地面监控系统、巷道监控系统与采煤机机载监控系统,并研究了各系统的软件和硬件及关键技术。研究为煤矿采煤机的智能控制提供了参考。     

直升机液冷/蒸发制冷联合系统关键部件试验性能

现代军用直升机经常执行特殊飞行任务，其机载电子设备具有功率大、瞬间振荡、高热通量等特点，使得环控系统的冷却需求呈指数上升趋势，进而制约着直升机的巡航功能和战斗性能的提升。针对直升机机载大功率电子设备的冷却需求，结合制冷剂、冷却液循环等子系统，搭建地面稳态试验台，针对蒸发器、冷凝器等关键部件进行了地面稳态试验。研究过程采用仿真与试验相结合的方法，开展了制冷循环中蒸发器、冷凝器等关键部件稳态仿真计算，且完成了蒸发器、冷凝器的换热性能试验研究，对所建立的仿真模型进行了有效性校核与参数修正。上述研究可为后续直升机液冷/蒸发制冷系统的关键部件设计提供一定的参考。     

基于电化学原理的飞机燃油箱氧浓度机载测量技术

飞机燃油箱惰化系统属飞机燃油系统设计中重要的分系统，为了准确评估燃油箱惰化系统的功能与性能，需要根据飞机实际使用剖面和惰化系统设计特点确定适用的飞行测试方法。提出了一种基于电化学原理的飞机燃油箱氧浓度机载测量方法，用于飞行实时测量运输类飞机油箱内无油空间或惰化管路的气体氧浓度，并对飞行中的实际影响因素进行模拟分析。经过分析飞行实际环境影响因素、关键传感器匹配性以及原理样机的试验验证等工作，将燃油箱氧浓度机载测量技术转化为专用的飞机燃油箱氧浓度机载测量系统，并通过了飞行实测考验。试飞结果表明，该项技术能够实时准确测量运输类飞机各种状态下的燃油箱氧浓度，满足飞机燃油箱惰化系统的效能评估要求。     

Structural analysis and optimization of a tethered swept wing for airborne wind energy generation

In this paper, we present an aero‐structural model of a tethered swept wing for airborne wind energy generation. The carbon composite wing has neither fuselage nor actuated aerodynamic control surfaces and is controlled entirely from the ground using three separate tethers. The computational model is efficient enough to be used for weight optimisation at the initial design stage. The main load‐bearing wing component is a nontypical “D”‐shaped wing‐box, which is represented as a slender carbon composite shell and further idealised as a stack of two‐dimensional cross section models arranged along an anisotropic one‐dimensional beam model. This reduced 2+1D finite element model is then combined with a nonlinear vortex step method that determines the aerodynamic load. A bridle model is utilised to calculate the individual forces as a function of the aerodynamic load in the bridle lines that connect the main tether to the wing. The entire computational model is used to explore the influence of the bride on the D‐box structure. Considering a reference D‐box design along with a reference aerodynamic load case, the structural response is analysed for typical bridle configurations. Subsequently, an optimisation of the internal geometry and laminate fibre orientations is carried out using the structural computation models, for a fixed aerodynamic and bridle configuration. Aiming at a minimal weight of the wing structure, we find that for the typical load case of the system, an overall weight savings of approximately 20% can be achieved compared with the initial reference design.     

面向航空通信应用的边沿触发器教学设计

研究和分析了面向航空通信应用的边沿触发器教学设计。以边沿触发电路实现原理为核心,引导边沿触发机制的探究式学习；以航空机载网络通信为具体应用背景,引入科学研究和工程实现中实际问题,设计曼切斯特码检测系统实验；使得边沿触发器教学成为“知识再创造”的过程和创新实践的新载体,以期培养新工科背景下的独立、创新和实践精神。     

虚拟战场环境的导弹可视化仿真设计

主要对多模复合制导仿真平台中的导弹视景仿真模块的实现方法进行了研究,介绍了仿真模块的组成,研究了三维物体建模的方法并讨论如何实现动态演示。对基于VC＋＋以OpenGL编程建模仿真和采用Creator、Vega实现作战导弹飞行可视化这样两种方法,概括阐述了其实现过程,并进行了分析比较,得到了适用于导弹飞行仿真控制的设计方法,对于其它场景下三维物体仿真具有一定的借鉴作用。