发动机整体多级转子盘深内腔加工技术

为了提高发动机的推重比和可靠性,目前大型航空发动机的风扇盘和压气机盘大多采用整体多级盘结构,整体锻件多级转子盘便是其中的一类。该盘重量轻、性能好,但其深内腔加工是一大技术难点。本文介绍了一种先进的深内腔加工方法和加工中应特别注意的问题,并提出了应用整体锻件机械加工整体多级转子,该转子不仅可以达到发动机结构减化和减重的目的,还可以利用现有设备加工,从而使我们免受诸如线性磨擦焊加工技术和设备等国外对我们在整体叶盘生产技术上的封锁和限制,为此,发动机整体多级转子盘深内腔加工技术应引起我国航空发动机行业相关人员的重视。     

基于非协调单元的液体火箭发动机推力室热结构分析

用巴兹公式和发动机的热力计算数据,得到了推力室内的燃气壁面对流传热系数和燃气温度的分布,并用有限单元法计算了推力室的温度场.在温度场计算基础上,采用Wilson非协调单元,对推力室的应力场进行了计算,其中位移函数采用二阶形式,将计算精度提高到二阶.结果表明:相比常规单元,Wilson非协调单元在计算结构比较复杂,温度梯度比较大的结构时,精度比较高,结果合理.      

国军标电磁兼容检测实验室间的能力比对

详细介绍了国军标电磁兼容检测实验室进行实验室间比对的方案,比对器具的选择和比对数据的处理方法,分析了国军标电磁兼容实验室比对的特点,用平均值、数据偏差等参数对国防系统实验室4个比对项目的数据进行了分析,研究实验室间测试结果存在差异的原因,并给出改进建议。     

示波器自动检定系统的设计

介绍示波器自动检定系统的组成及原理框图,系统软件设计及特点。     

热电偶、热电阻自动检定系统的设计与实现

介绍了热电偶、热电阻系统的工作原理及其硬件组成、软件实现,并简要叙述了其自动检定的过程及方法。     

基于X波段雷达海浪监测装置的设计与研究

针对舰船对浪高实时测量的需要,提出了基于x波段雷达海浪监测装置的设计方案,具体介绍了基于X波段雷达海浪监测装置的设计原则、功能设计、硬件设计以及基于VC 的软件实现,并给出基于x波段雷达海浪监测装置系统操作平台功能界面的参考实例,从一定程度上为舰船海浪测量装置的实现与应用提供可行性参考。     

Generic procedure for designing and implementing plan management systems for space science missions operations

This paper is one of the components of a larger framework of activities whose purpose is to improve the performance and productivity of space mission systems, i.e. to increase both what can be achieved and the cost effectiveness of this achievement. Some of these activities introduced the concept of Functional Architecture Module (FAM); FAMs are basic blocks used to build the functional architecture of Plan Management Systems (PMS). They also highlighted the need to involve Science Operations Planning Expertise (SOPE) during the Mission Design Phase (MDP) in order to design and implement efficiently operation planning systems. We define SOPE as the expertise held by people who have both theoretical and practical experience in operations planning, in general, and in space science operations planning in particular. Using ESA’s methodology for studying and selecting science missions we also define the MDP as the combination of the Mission Assessment and Mission Definition Phases. However, there is no generic procedure on how to use FAMs efficiently and systematically, for each new mission, in order to analyse the cost and feasibility of new missions as well as to optimise the functional design of new PMS; the purpose of such a procedure is to build more rapidly and cheaply such PMS as well as to make the latter more reliable and cheaper to run. This is why the purpose of this paper is to provide an embryo of such a generic procedure and to show that the latter needs to be applied by people with SOPE during the MDP. The procedure described here proposes some initial guidelines to identify both the various possible high level functional scenarii, for a given set of possible requirements, and the information that needs to be associated with each scenario. It also introduces the concept of catalogue of generic functional scenarii of PMS for space science missions. The information associated with each catalogued scenarii will have been identified by the above procedure and will be relevant only for some specific mission requirements. In other words, each mission that shares the same type of requirements that lead to a list of specific catalogued scenarii can use this latter list of scenarii (regardless of whether the mission is a plasma, planetary, astronomy, etc. mission). The main advantages of such a catalogue are that it speeds-up the execution of the procedure and makes the latter more reliable. Ultimately, the information associated to each relevant scenario (from the catalogue or freshly generated by the procedure) will then be used by mission designers to make informed decisions, including the modification of the mission requirements, for any missions. In addition, to illustrate the use of such a procedure, the latter is applied to a case study, i.e. the Cross-Scale mission. One of the outcomes of this study is an initial set of generic functional scenarii. Finally, although border line with the above purpose of this paper, we also discuss multi-spacecraft specific issues and issues related to the on-board execution of the plan update system (PUS). In particular, we show that the operation planning cost of N spacecraft is not equal to N times the cost of 1 spacecraft and that on-board non-synchronised operation will not require inter-spacecraft communication. We also believe that on-board PUS should be made possible for all missions as a standard.     

军用车辆外部射频干扰试验测试技术研究CSCD

提出了军用车辆外部射频干扰测试平台的搭建方法,对发射天线的选择、输入功率计算及测试系统匹配进行了详细介绍。给出了相应的测试方法,归纳该方法的技术特点及创新点。结合该测试平台及测试方法对抗干扰指标要求进行了验证。     

一种具有高抗干扰能力高速数据链的设计与实现

简要介绍了数据链的基本概念和国内外发展状况,根据实际作战模式需求给出总体设计方案。详细给出了系统构架及设备组成,采用模块化设计方案,实现设备的通用化、小型化和轻质化。着重提出基于群聚（Orthogonal Frequency Division Multiplexing,OFDM）技术方案,以解决低仰角抗多径高速数据传输应用需求。实验结果表明总体方案可行,可以在后续武器型号中投入使用。     

模块化可重构无人机机翼结构优化方法研究

模块化可重构无人机设计工况复杂、约束多样,需要根据不同设计思想的特点研究适用的优化方法才能得到最优方案。本文开展针对多模型的同步优化方法研究,给出不同构型机翼翼根弯矩约束方法,提出多构型机翼结构前后梁弯矩比例约束下的同步优化技术,并以某模块化可重构无人机机翼为对象进行应用验证。结果表明：与文献中模块化机翼优化结果相比,本文多构型机翼结构同步优化方法在解决整机翼更换的模块化可重构机翼结构优化问题时具有很高的适用性和收敛性,以及广阔的工程推广价值。