对抗高超声速武器的机载激光武器发展研究

介绍了高超声速武器对现有军事防御系统的威胁,机载激光武器对抗高超声速武器的军事价值。详细描述了国外机载激光武器的研究进展以及研究机载激光武器的技术难点,指出当前研究机载激光武器必须进一步降低激光武器的重量和体积,研发动态环境的光束控制与瞄准跟踪系统,开展特殊气动布局设计研究,建立周密的能源管理系统。     

机载激光武器自卫防御应用研究与前景分析

对来袭防空战术导弹进行干扰毁伤,实现载机的自卫防御是机载激光武器的重要应用方向之一。本文简要对国外主要防空战术导弹的发展历程、技术特点以及作战能力进行了概述,结合激光作用机理阐述了激光武器对导弹的干扰毁伤特点,在此基础上对机载平台自卫防御激光武器的作战应用能力需求进行了研究,描述并分析了目前机载激光武器发展现状,并对机载自卫激光武器的影响与挑战进行了综合评估分析。     

机载激光武器储能供电研究

激光武器作战时瞬时功耗500～700kW,目前机载供电很难直接满足需求,为了满足机载激光武器高功率输出的作战需求,在机载发电机和激光武器能量输入级之间需要进行高能储存。针对100kW激光输出功率,分析激光武器系统用电需求,通过供电方式及储能装置对比,提出以机载发电机、储能装置及激光器激励源组合供电思路,比较飞轮储能和电池/超级电容组合储能两种可实施方案,并利用超级电容器组作为储能装置开展了机载激光武器供电技术研究,验证了机载超级电容储能供电的可行性。     

美国空中激光武器发展现状

近年来,美国导弹防御局(MDA)和国防部预研局一直在推动化学激光武器的发展,其中包括两个空中激光武器系统,即"机载激光武器"(ABL)计划和"先进战术激光武器"(ATL)计划,目前这两个计划都已经或即将开始飞行测试.另外,美国空军还开展了一种新型激光派生技术的发展,即使用空中中继反射镜克服地平线的限制,将激光的射程延伸到更远的地方.     

空气动力学发展中值得关注的一些问题

本文阐述了空气动力学研究的特点；分析了21世纪初空气动力学面临的形势，提出了空气动力学发展中值得关注的一些问题，包括新流型的研究与先进气动布局、流动控制与增升减阻、流动的逢适应控制与智能化空气动力学、低雷诺数流动与微流体力学、等离子体减阻技术、等离子体隐身与电空气动力学、机载激光武器的发展与气动光学等。     

机载激光武器系统的应用研究

机载激光武器系统是一种应用于现代战机的高能武器系统.作为一种新型武器系统,机载激光武器系统倍受世界各军事强国的关注,积极的从事应用研究有重大的意义.本文在介绍机载激光武器系统的基础上,对机载激光武器系统应用的关键技术及需要考虑的问题、战术应用进行了分析和研究.     

飞行的激光炮

高功率激光武器不仅是防御性武器,可用于战略防御、战区防御和战术防空,而且是进攻性武器,特别适用于反导弹、反卫星,以及精确打击和非致命打击。激光武器以光速攻击目标的独特本领,将导致未来战场发生革命性变化,使之成为21世纪最主要的新概念武器之一。美国国防部和美国空军认为,机载战术激光武器比车载激光武器更加机动灵活,是快速发展的一种新概念武器,可作为致命武器和非致命武器打击战略、战术目标。机载战术激光武器作为     

基于成像跟踪的激光瞄准

研究了强激光武器系统中基于激光光斑对目标跟踪瞄准的一种新方法。讨论了先用弱光斑对目标上的攻击部位进行稳定精跟踪瞄准,再增大激光功率摧毁目标的激光武器新的攻击模式。并为此提出“基于成像跟踪的激光瞄准”的概念。介绍了基于成像跟踪的激光瞄准技术的原理,理论分析表明该方法可以用于对5km外的反舰导弹进行侧向拦截。     

国外10MW风力机叶片气动布局研究

降低风能利用成本是风力机单机装机功率向大型化发展的主要驱动力,10MW风力机已成为当今国外大型风力机研发的目标。本文简要回顾了风力机叶片空气动力研究对风力机大型化发展的贡献,探讨国外针对10MW风力机开展的新型叶片气动布局研究。     

机载激光武器的研发

简要介绍了机载化学激光武器及电子激光武器的研发历史及现状.     

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.