基于AD590组成的温度测量电路及应用

AD590是AD公司利用PN结正向电流与温度的关系制成的电流输出型两端温度传感器。由于该器件具有良好的线性特性和互换性，因此测量精度高，并具有消除电源波动的特性。通过分析AD590的基本结构、主要性能以及基本工作原理，介绍了该器件在温度检测中的广泛应用。     

一种EFPI光纤压力传感器的结构分析及零点稳定性

介绍了一种基于法布里-珀罗干涉原理的EFPI光纤压力传感器。详细分析了这种光纤压力传感器的原理、结构和解调方法;讨论分析了材料、结构以及制作工艺对零点稳定性的影响;探讨了传感器内部热应力的分布以及消除方法。该结构传感器在经历-40℃和400℃的严酷温度考验后,零点漂移小于3 nm。     

复合材料缺陷的红外热波无损检测

简述了红外热波无损检测的原理，并利用红外热波无损检测系统对铝蜂窝夹芯结构复合材料和泡沫夹芯结构复合材料的胶接界面脱粘缺陷进行了检测。结果表明，该方法检测此类缺陷快速、高效、直观。引入界面层的概念，建立了此类复合材料缺陷红外热波检测的数学分析模型，利用该模型简单方便地对热像图进行了理论分析。     

基于拉曼散射的分布式光纤温度传感技术的研究

论述了基于拉曼散射的分布式光纤温度传感器的基本工作原理、结构、系统特点及信号处理方法。该结构及信号处理方法具有一定的空问分辨率，保证了系统的实用性。将分布式光纤传感器与传统的复用温度光纤传感器阵列进行了比较。通过使用分布式光纤温度传感器信号处理系统和信号处理软件相结合进行实验，得出结论。     

新型减振阻尼器的研制

本文介绍一种新型振动控制元件──电流变体阻尼器。该阻尼器基于小孔节流原理，利用具有固液两相特性的新型材料──电流变体研制而成，其输出力矩大小可由电信号直接控制，响应迅速。作者在文中对阻尼器的结构原理、理论模型以及性能测试情况进行了介绍。     

基于亚历山大效应的光谱高温仪校准方法研究

介绍了亚历山大效应,分析了基于该效应的光谱高温仪的温度测量原理,即"温度-光谱-色彩角"的关系,建立了光谱高温仪光谱测量模型,提出了3000℃以下温度范围的光谱高温仪的校正方法,以及3000℃以上的光谱高温仪校正路径。     

液体火箭发动机低温阀门铝垫片密封性能数值分析

为研究某液体火箭发动机低温阀门铝垫片密封结构在低温工作环境下的密封性能，利用Abaqus软件建立了该结构的二维轴对称模型，计算了低温工作状态下铝垫片密封表面接触压力的变化，并研究了铝垫片在循环温度载荷作用下接触压力下降的机理。结果表明，在低温工作时密封垫片与阀门各部件材料线胀系数不同导致了在温度降低时密封面上的接触力的下降；而铝垫片密封表面上复杂的应力应变状态导致接触压力在温度载荷作用下无法恢复。在温度载荷循环作用下，铝垫片密封面上产生了棘轮效应。垫片的塑性应变在棘轮效应中累积且最大应力值在棘轮效应中下降；接触力会随着温度载荷循环次数增加逐步降低并在一定周期后保持稳定。提出了采用锥形垫片的结构改进方案，并通过仿真验证了该结构在循环温度载荷作用下保持密封压力的有效性。     

浮动零点法及其在声表面波（SAW）传感器中的应用

温度是影响传感器精度的重要因素。本文介绍了一种新的温度误差校正方法，即浮动零点法。该方法以差动原理和浮动坐标为基础，是实现温度校正较为理想的方法。     

InSb磁敏电阻角位移传感器的研究

简单分析了InSb磁敏电阻的工作原理，讨论了利用偏置磁场作用于半桥磁敏电阻构成转动速度及位移传感器的测试原理；针对半导体材料对温度十分敏感的特点，提出了利用浮动零点跟踪技术测试齿轮转速的方法，并对其优缺点进行了讨论。     

浅谈波音737-800飞机空调负载对发动机起飞推力的影响

介绍了波音737-800飞机空调负载状态影响发动机起飞推力限制的原理,以及空调组件活门位置传感器故障导致左右发动机N1限制值显示不一致的原因,同时还介绍了减推力起飞的概念以及假定温度选择范围的限制,并通过实例分析了在减推力起飞时假定温度不在可选择范围之内时该原理的应用。     

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.      

ν-gap度量及其在飞行控制律评估中的应用

 传统控制律评估方法主要用于单输入单输出（SISO）系统，且对模型参数摄动考虑不够全面,针对这些不足，研究了ν-gap度量方法。在介绍系统广义稳定裕度相关概念的基础上，给出了ν-gap度量的定义、特点和性质以及近似摄动模型的计算，提出ν-gap度量评估控制律的步骤。实例结果表明，该方法不仅克服了上述传统评估方法的缺陷，而且还有根据所求的各摄动影响情况忽略影响小的元素，以减少计算量及可以找到最坏情况下的参数摄动组合等优点。     

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。     

Integrated Entry Guidance for Reusable Launch Vehicle

A method for the implementation of integrated three-degree-of-freedom constrained entry guidance for reusable launch vehicle is presented. Given any feasible entry conditions, terminal area energy management interface conditions, and the reference trajectory generated onboard then, the method can generate a longitudinal guidance profile rapidly, featuring linear quadratic regular method and a proportional-integral-derivative tracking law with time-varying gains, which satisfies all the entry corridor constraints and meets the requirements with high precision. Afterwards, by utilizing special features of crossrange parameter, establishing bank-reversal corridor, and determining bank-reversals according to dynamically adjusted method, the algorithm enables the lateral entry guidance system to fly a wide range of missions and provides reliable and good performance in the presence of significant aerodynamic modeling uncertainty. Fast trajectory guidance profiles and simulations with a reusable launch vehicle model for various missions and aerodynamic uncertain-ties are presented to demonstrate the capacity and reliability of this method.     

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。