B／A1复合材料的制造,性能及应用

综述了国内外Ｂ／Ａ１复合材料的发展研究现状,具体介绍了几种制备技术的基本原理和工艺包括热压扩散法、熔体浸渗法等。从工艺的角度分析了复合工艺参数－－温度、时间、压力和环境对Ｂ／Ａ１复合材料及对Ｂ纤维的影响。对Ｂ／Ａ１复合材料的力学性能和在航空航天等方面的应用也做了较为系统的介绍,分析认为国内采用热压扩散法制备的Ｂ／Ａ１复合材料性能稳定,其管材、型材已达到了应用阶段,为我国航空航天技术中应用此类复合材     

热等静压法制备B/Al复合型材的研究

介绍了热等静压法制Ｂ／Ａｌ复合型材的工艺过程,对热等静压法制备Ｂ／Ａｌ复合型材的工艺进行了探索研究,获得了制备Ｂ／Ａｌ复合型材,可一次成型多根质量符合要求的常用形式的Ｂ／Ａｌ复合型材。     

B／Al单向铺层复合板的力学性能及断裂行为的研究

研究了热压扩散结合工艺对Ｂ／Ａｌ复合材料的强度的影响,并对试样拉伸断口及断裂径进行了研究,分析表明,试样断口有三种断裂模型,断裂路径同热压工艺有密切的关系。     

特低燃速固体推进剂低压下的燃速测试

用“高低压声发射燃速测试系统”研究测定了特低燃速丁羟推进剂（ｒ＝２ｍｍ／ｓ～４ｍｍ／ｓ）在２ＭＰａ低压下的燃速和２ＭＰａ～１４ＭＰａ范围内的燃速压强指数。结果表明,特低燃速的测试精度可达１％,某ＨＴＰＢ－ＡＰ－Ａｌ－Ｔ２９－ＨＭＸ推进剂的燃速测试临界压强为２ＭＰａ。     

含燃速催化剂的丁羟推进剂高压燃烧性能研究

对含Ｔ２７（一种二茂铁衍生物）、卡托辛、Ｆｅ２Ｏ３三种燃速催化剂的ＨＴＰＢ／ＡＰ／Ａｌ推进剂在１６ＭＰａ～２２ＭＰａ下的燃速和燃速压强指数进行了研究。结果表明：二茂铁衍生物能大幅度提高ＨＴＰＢ／ＡＰ／Ａｌ推进剂的燃速,同时可使高压下的压强指数大幅度地下降;Ｆｅ２Ｏ３对ＨＴＰＢ／ＡＰ／Ａｌ推进剂有着显著的燃速催化效果,但其推进剂压强指数较高;Ｆｅ２Ｏ３的催化效率较Ｔ２７高,但不及卡托辛;Ｆｅ２Ｏ３和二茂铁衍生物组合使用能进一步提高ＨＴＰＢ／ＡＰ／Ａｌ推进剂的燃速,并使推进剂具有较低的压强指数。     

（Al2o3）p／Al复合材料的研究

本研究采用Ｌａｎｘｉｄｅ工艺制备了Ａｌ２Ｏ３颗粒增强铝基复合材料，分析了（Ａｌ２Ｏ３）ｐ／Ａｌ的微观结构，测试了铝基复合材料的拉伸性能、瞬时耐温性能、导热性能。结果表明，在渗透完全，显微结构致密；在Ａｌ２Ｏ３与Ａｌ的界面处，原位生成ＭｇＡｌ２Ｏ４尖晶石晶体复合材料的极限拉伸强度为３５０－３７８ＭＰａ，拉伸量为１０３－１２１．６ＧＰａ，断裂延伸率为１．９６％；在１０８０℃、２０ｓ的氧乙炔焰下，无烧蚀     

比WC／Co更硬的WC／NiAl复合材料

比ＷＣ／Ｃｏ更硬的ＷＣ／ＮｉＡｌ复合材料美国橡树岭国家实验室研制了一种比ＷＣ／Ｃｏ更硬的、强度更高的耐高温复合材料，该材料是碳化钨和铝镍合金化学结合的产物。其制造工艺是将碳化钨粉末的铝镍合金粉末配料混合，再经热压烧结而成，比种ＷＣ／ＮｉＡｌ新型复合材...     

NiAl合金基原位复合材料的反应热压法制备和拉伸性能

研究了反应热压技术（包括反应轴向热压（ＲＨＰ）和反应热等静压（ＲＨＩＰ）法）制备的Ｎｉ５０Ａｌ２０Ｆｅ３０（ＮｉＡｌ（Ｆｅ））基原位复合材料的微观组织和拉伸性能。结果表明,反应热压技术制备的ＮｉＡｌ（Ｆｅ）基复合材料中原位合成的ＴｉＣ颗粒细小,分布均匀、弥散,但复合材料不完全致密,孔隙的存在损害了其拉伸性能。二次加工工艺可提高ＮｉＡｌ（Ｆｅ）基原位复合材料的致密性和组织均匀性,从而显著改善其力学性能。     

锡青铜与钢的扩散连接

研究了ＱＳｎ４－４－２．５锡青铜与４５＾＃钢的扩散连接,以及工艺参数对接头性能的影响,确定了锡青铜与钢扩散连接的最佳工艺参数：连接温度Ｔ＝８２０℃－８５０℃,连接压力Ｐ＝１．０ＭＰａ－２．０ＭＰａ,连接时间ｔ＝２０ｍｉｎ,接头抗拉强度可达１８０Ｍａ以上,并运用金相,扫描电镜对接头进行了微观分析。     

热塑性聚氨酯弹性体及推进剂生成焓的估算

为了解决以热塑性聚氨酯（ＴＰＵ）为粘合剂制备的新型热塑性推进剂配方能量的计算问题,以Ｖａｎ Ｋｒｅｖｅｌｅｎ和Ｃｈｅｒｍｉｎ等人的基因估算方法及数据为基础,结合高分子内聚能的概念,从理论上探索了一条估算热塑性聚氨酯生成焓的方法,得到了ＴＰＵ的生成焓与硬段含量之间的关系式,并对４５％ＴＰＵ／Ａｌ／ＡＰ复合热塑性推进剂的能量水平进行了计算。计算表明：体系组成为ＴＰＵ／ＡＰ／Ａｌ＝１４／６２／２４时,出     

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.     

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）。     

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.      

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.