超标量RISC芯片88110得到军方的重视

超标量ＲＩＳＣ芯片８８１１０得到军方的重视１９９３年３月，Ｍｏｔｏｒｏｌａｊｂ司军事产品开发部决定出售基于超标量ＩＲＳＣ８８１１０军用规范芯片的多芯片模块（ＭＣＭ），这种模块采用了ＩＢＭ／ｋ司的Ｃ．“例装式”４块技术。这一决定的背景是：美国高性能计算...     

从FMS走向RMS--可重配制造系统(中)

5　可重配机床 (ＲＭＴ)如前所述 ,ＲＭＳ由ＲＭＴ和ＲＣＳ两大部分组成。ＲＭＴ是一种新型、基于机床模块库中的机床模块的集成来实现机床设计的方法。每一种机床模块能够提供一种基本运动 ,这是一种将机床设计转换成通过对机床模块合理选择的数学处理方法 ,可产生出新类型的机床。机床模块化设计技术已存在好多年了 ,但从构造制造系统的观点看 ,则是最近几年才提出的。模块化设计技术已被许多设备制造商在现行机床(特别是在数控加工中心、车削中心和ＦＴＬ设备 )设计中采用。一种面向模块对象 (如主轴、进给驱动装置、结构件部件 )和结构…     

用DSC曲线求EML─2，4固化环氧树脂的动力学参数

ＥＭＩ─２，４固化环氧Ｅ─５１的反应是由三个基本反应组成的复杂反应。本文用一张ＤＳＣ图，在二者质量比为０．０４２３６６时，求出其固化反应的表观动力学参数：ｎ＝０，Ｅ＝１．８１×１０￣５Ｊ／ｍｏｌ，Ａ＝３．４×１０￣２２ｓ￣－１。并发现二者质量比在２５％附近时．ＤＳＣ图出现双峰；固化剂用量不同时有不同的动力学参数。     

Si_3N_4－SiC纤维先驱体──低分子量聚硅氮烷的合成与分析

以Ｍｅ_２ＳｉＣｌ_２、ＭｅＳｉＨＣｌ_２（式中Ｍｅ代表ＣＨ_３）或其混合物与ＮＨ_３反应制得低分子量聚硅氮烷，该产物是制备Ｓｉ_３Ｎ_４－ＳｉＣ纤维先驱体的基本原料。研究了不同配比的Ｍｅ_２ＳｉＣｌ_２／ＭｅＳｉＨＣｌ_２混合物氨解反应所需的时间，氨解产物的物理性能、分子量及其分布，着重分析了氨解产物的结构。     

总线接口模块小型化与机载电子设备可靠性增长

增长机载电子设备可靠性指标的有效途径之一是数字电路的小型化。本文通过计算航空电子总线接口模块（ＭＢＩ）的小型化过程三个阶段（采用中小规模集成电路设计ＭＢＩ；采用超大规模集成电路和ＡＳＩＣ技术设计ＭＢＩ；采用ＳＭＴ表面封装和二次集成技术设计ＭＢＩ）的可靠性预计指标，说明数字电路小型化可以使机载电子设备可靠性增长。     

Si3N4—SiC纤维先驱体——低分子量聚硅氮烷的合成与分析

以ＭｅＳｉＣｌ２（式中Ｍｅ代表ＣＨ３）或共混合物与ＮＨ３反应制得低分子量聚硅氮烷，该产物是制备Ｓｉ３Ｎ４－ＳｉＣ纤维先驱体的基本原料。研究了不同配比的Ｍｅ２ＳｉＣｌ２／ＭｅＳｉＨＣｌ２混合物氨解反应所需的时间，氨解产物的物理性能、分子量及其分布，着重要分析了氨解产物的结构。     

浅谈柔性制造系统的建立

柔性制造系统（ＦＭＳ）是一种高效率、高自动化的产品生产制造系统。本文从市场需求分析着手，叙述了建立ＦＭＳ的步骤、内容，各模块之间的协调以及ＦＭＳ的经济评价；简单介绍了ＦＭＳ在国外的发展状况；展望ＦＭＳ的发展。     

IGHz Power4芯片整装待发

ＩＢＭ在ＨｏｔＣｈｉｐｓ大会上首次展出了其ＩＧＨｚ测试版芯片Ｐｏｗｅｒ４，准备装备其ＡＳ／４００和ＲＳ／６０００服务器系列产品。ＩＢＭ同时还开发了同步液流水线接口相补充，使Ｐｏｗｅｒ４的总线速度超过５００ＭＨｚ．ＩＢＭ称，Ｐｏｗｅｒ４的目的不仅是推出一款高性能处理器，而且是一种高性能服务器．ＩＢＭ希望Ｐｏｗｅｒ４能够用于Ｗｅｂ服务器中，运行电子商务应用软件或复杂的科技和工程应用软件。ＩＢＭ装备新处理器的ＡＳ／４００及ＲＳ／６０００服务器要到２００１年下半年才能出台．Ｐｏｗｅｒ４在一块芯片上容纳了…     

MBI软件的标准化及规范化设计

ＭＢＩ作为多路传输总线接口模块，能够实现ＭＩＬ－ＳＴＤ－１５５３Ｂ协议，完成航空电子子系统之间的连接，在通信软件的支持下完成航空电子子系统之间的通信。本文将详细介绍为机载设备ＤＴＳ的ＭＢＩ接口模块配置的通信软件的标准化及规范化设计。     

热塑性树脂基复合材料（C／PI）的初步研究

本文以热塑性非结晶性聚酰亚胺树脂为基体，以Ｔ３００和ＡＳ－４两种碳纤维进行复合增强。探索了制作工艺，对层压复合材料进行力学性能测试，并彩和动态力学方法（ＤＭＡ）深入研究。实验表明，高温成型（４００℃左右）的复合材料应采用耐氧化碳纤维增强，不同升温速率测得的ＤＭＡ图谱不同。当测试条件接近使用条件时可判断的可靠性及使用范围。     

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.