飞机电缆敷设

在飞机上 ,电线电缆的合理敷设是减小设备间电磁耦合的有效措施。本文分析了扭绞线、屏蔽线和同轴电缆的抗干扰特性 ,介绍了电线电缆的分类 ,以及各类线间的最小间距。最后 ,讨论了电缆屏蔽层的接地方式对电磁耦合的影响     

制造业经理人

博而精,传承优良品质毕博姆特是特别擅长于机械工程学设计以及各类产品生产制造的瑞士公司。对于毕博姆特来说,我们做的不仅是设备的输出,更是技术的输出;我们不仅有自己的技术,还会为客户提供量身定做方案,曾经为欧洲空客、波音等专门设计了许多产品。毕博姆特的产品主要有多轴头、直角铣头、万能铣头、非标铣头、刀塔以及各类大扭矩、增速器等,     

机载用电设备的供电适应性试验系列标准制定与实施

机载用电设备的供电适应性试验是对各类机载用电设备在各种供电状态下的性能以及用电设备工作对供电系统影响的验证，是保证用电设备（尤其是大功率电子设备）与飞机供电系统相兼容的重要措施和方法。本文阐明了我国机载用电设备的供电适应性试验系列标准的组成和相互关系，着重对供电适应性试验方法标准的定位、框架、结构要素的确定和主要内容进行了分析，并提出实施供电适应性方法标准的建议。     

用高技术实施精确空投

现代战争需要快速、精确、秘密、低成本以及低损耗地将物资和人员投放到指定的区域,这也是军事后勤革命的重要组成部分。近年来,通过将 GPS/惯性导航系统引入降落伞设计,开发了自主导引伞降系统、伞兵定位器等设备,以及将伞降系统并入网络的做法,大大提升了各类空投的精确性。     

西飞颁发两年度总经理创新奖

近日，西飞技装、数控中心、机加、钣金等生产单位的设备管理人员和现场维护人员在刚刚开通的西飞设备管理系统中轻点鼠标，即可完成各类信息的整理和传递。西飞设备管理系统基于西飞ERP平台，历时两年开发完成。该系统不仅即时提供了西飞各类设备资源的状况，同时对设备运行、故障、事故等信息进行即时采集，为管理部门应对突发事故、计算设备的可利用率、平均故障时间和设备故障率提供依据，并对降低设备故障率，     

面向未来飞机的机载网络存储系统研究

根据未来飞机航电系统的拓扑结构以及机载各类数据特征,提出了一种高性能、高吞吐量和高可靠性的机载网络存储系统设计方法,从而满足了未来飞机对高性能存储系统的需求,允许机载各个设备客户端对服务器进行透明的文件访问,实现了跨平台的数据共享,为网络存储系统关键技术在航空产品上的进一步应用提供了技术基础。     

应用ACCESS2000构建工装、测试设备管理信息系统

论述了基于ACCESS2000的“工装、测试设备管理信息系统”的开发。通过该系统,设备管理人员可方便地对各类设备的各种情况进行查询,改变了以往人工模式,并实现了统一管理,大大提高了工作效率。     

可靠性与环境实验室简介(1)

中国航空无线电电子研究所可靠性与环境实验室是在中国航空工业部华东地区环境试验站基础上发展起来的,地处上海漕河泾高新技术开发区,承担着产品的可靠性与环境实验,产品可靠性设计分析以及试验技术研究等工作。实验室拥有一支作风优良,技术精湛的队伍,共有各类员工19名,其中大学本科9名。实验室场地面积约1000m2,拥有各类环境实验设备16台套。     

“鲨鱼皮”涂料、增强现实等多种创新产品即将进入维修领域

当OEM、航空公司下属维修企业以及独立维修企业致力于研发各类新维修设备和新服务项目时，维修领域技术创新的脚步也从未停歇，如增材制造技术（又称ALM或3D打印）、新型涂料、先进的发动机清洗技术以及增强现实技术都是榜上有名。     

精密旋转设备静、动平衡量测试方法研究

对精密旋转设备的静、动平衡原理进行了深入分析,提出了相应的测量方法;为了减小对主轴回转精度的影响,进行了双校正面的动平衡系统设计和整机的静平衡系统设计,其结论对各类精密旋转设备总体结构和主轴系统设计具有指导意义。     

有翼高超声速再入飞行器气动设计难点问题

有翼高超声速再入飞行器是近年来的研究热点,气动设计是飞行器设计的关键。为了更清楚地认识有翼高超声速再入飞行器气动设计的难点问题,对有翼高超声速再入飞行器的发展、优势及总体任务剖面进行了介绍,从5个方面详细介绍了该类飞行器气动设计的难点问题,包括多约束复杂面对称气动布局设计、高温真实气体效应对气动特性影响、天地差异与天地换算方法、反作用控制系统(RCS)喷流干扰对气动特性的影响以及气动数据不确定度等,简要阐明了这些难点问题对总体设计的重要性以及初步的解决思路,为有翼高超声速再入飞行器气动设计提供了一些参考。     

Simulation and Analysis of Crashworthiness of Fuel Tank for Helicopters

Crashworthiness requirement of fuel tanks is one of the important requirements in helicopter designs. The relations among the protection frame, textile layer and rubber layer of the fuel tank are introduced. Two appropriate FE models are established, one is for an uncovered helicopter fuel tank without protection frame, and the other is for fuel tank with protection frame. The dynamic responses of the two types of fuel tanks impinging on the ground with velocities of 17.3 m/s are numerically simulated for the purpose of analyzing energy-absorbing capabilities of the textile layer and protection frame. The feasibility of the current crashworthiness design of the fuel tank is examined though comparing the dynamic response behaviors of the two fuel tanks.     

The effect of inlet conditions on the flow and heat transfer in multiple rotating cavity with axial throughflow

This paper discusses experimental results from two different build configurations of a heated multiple rotating cavity test rig.Measurements of heat transfer from the discs and tangential velocities are presented.The test rig is a 70% full scale version of a high pressure compressor stack of an axial gas turbine engine.Of particular interest are the internal cylindrical cavities formed by adjacent discs and the interaction of these with a central axial throughflow of cooling air.Tests were carried out for a range of non-dimensional parameters representative of high pressure compressor internal air system flows(Re up to 5×106 and Rez up to 2×105).Two different builds have been tested.The most significant difference between these two build configurations is the size of the annular gap between the(non-rotating) drive shaft and the bores of the discs.The heat transfer data were obtained from thermocouple measurements of surface temperature and a conduction solution method.The velocity measurements were made using a two component,LDA system.The heat transfer results from the discs show differences between the two builds.This is attributed to the wider annular gap allowing more of the throughflow to penetrate into the cavity.There are also significant differences between the radial distributions of tangential velocity in the two builds of the test rig.For the narrow annular gap,there is an increase of non-dimensional tangential velocity V/Ωr with radial location to solid body rotation V/Ωr=1.For the wider annular gap,the non-dimensional velocities show a decrease with radial location to solid body rotation.      

突破技术趋同，波音再现竞争优势

 波音公司面临着来自空客公司的巨大挑战,企业战略性创新才是公司成功的关键。为此波音公司的全部战略性研究集中在扩大产品的差异性上,体现在3个方面：电子化（e-Enabled）运营环境、整体复合材料机身部件的制造技术和支持波音787客机的全球协同环境（GCE）。     

临近空间飞行器测控与信息传输系统频段选择

 临近空间飞行器是高性能信息化武器平台,测控（TT&;C）与信息传输系统是其信息保障的核心,而选择合理、可行的频段是展开系统设计的前提和基础。频段选择影响到整个技术方案的制定,是一个需综合考虑、影响深远并具有战略意义的关键问题,从国际电联（ITU）国际标准、高速数传、接收信噪比（SNR）、“三抗”、超视距中继、黑障、雨衰以及设备研制成熟度8个方面全面、细致论证了近空间平台测控系统的频段选择问题,最终得出在视距链路中以Ka频段为宜,在超视距链路中以Ku/Ka双频段为宜的结论。     

基于弯曲激波压缩系统的高超声速进气道反设计研究进展

总结了近十年来弯曲激波压缩研究的主要成果。提出了弯曲激波压缩系统的新概念,即利用特殊设计的楔形弯曲压缩面或空间弯曲压缩面,产生一系列与前缘弱激波相互交汇或叠加的压缩波系,从而使前缘激波弯曲,形成特殊的弯曲激波,它与波后的等熵压缩波来共同完成对气流的压缩。在此基础上,实现了由给定出口气动参数的超声速内流道反设计,实现了由给定压缩面压力分布和给定压缩面马赫数分布要求的型面反设计,实现了由给定激波波面的压缩型面反设计。研究证明,弯曲压缩面-弯曲激波压缩系统具有良好的综合气动性能,为高性能高超声速进气系统的气动设计提供了一种全新的设计方法。     

Experimental Study on Effects of Fuel Injection on Scramjet Combustor Performance

In order to investigate the effects of fuel injection distribution on the scramjet combustor performance, there are conducted three sets of test on a hydrocarbon fueled direct-connect scramjet test facility. The results of Test A, whose fuel injection is carried out with injectors located on the top-wall and the bottom-wall, show that the fuel injection with an appropriate close-front and centralized distribution would be of much help to optimize combustor performances. The results of Test B, whose fuel injection is performed at the optimal injection locations found in Test A, with a given equivalence ratio and different injection proportions for each injector, show that this injection mode is of little benefit to improve combustor performances. The results of Test C with a circumferential fuel injection distribution displaies the possibility of ameliorating combustor performance. By analyzing the effects of injection location parameters on combustor performances on the base of the data of Test C, it is clear that the injector location has strong coupled influences on combus- tor performances. In addition, an inner-force synthesis specific impulse is used to reduce the errors caused by the disturbance of fuel supply and working state of air heater while assessing combustor performances.     

(高)超声速流动试验技术及研究进展

近年来,与高速飞行器相关的(高)超声速流动受到了极大的关注。这类流动所具有的非定常性、强梯度和可压缩性对试验方法和风洞设计技术提出了挑战。超声速纳米示踪平面激光散射(NPLS)技术是由作者所在团队研发的非接触光学测试技术。它能够以较高的空间分辨率来揭示超声速三维流场的一个瞬态剖面的时间解析的流动结构。介绍了NPLS技术以及基于NPLS开发的密度场测量、雷诺应力测量和气动光学波前测量等方法,并回顾了这些技术在超声速边界层、超声速混合层、超声速压缩拐角、激波/边界层相互作用和光学头罩绕流等流动中的应用,清晰地再现了边界层、混合层、激波等典型流场结构及其时空演化特性。另外,为了模拟和研究高空大气条件下边界层自然转捩和超声速混合层的转捩特性,介绍了高超声速静风洞、超-超混合层风洞的设计技术以及层流化喷管的设计方法。     

Research on Auto-detection for Remainder Particles of Aerospace Relay Based on Wavelet Analysis

Aerospace relay is one kind of electronic components which is used widely in national defense system and aerospace system. The existence of remainder particles induces the reliability declining, which has become a severe problem in the development of aerospace relay. Traditional particle impact noise detection (PIND) method for remainder detection is ineffective for small particles, due to its low precision and involvement of subjective factors. An auto-detection method for PIND output signals is proposed in this paper, which is based on direct wavelet de-noising (DWD), cross-correlation analysis (CCA) and homo-filtering (HF), the method enhances the affectiv-ity of PIND test about the small particles. In the end, some practical PIND output signals are analysed, and the validity of this new method is proved.