NO激光诱导荧光对高焓气流温度的测量

由于真实气体效应，高超声速流场的研究仍然依赖于大量的实验.流场温度是实验的重要参数，目前只能通过具有非入侵性质的光学测量手段获得，然而，由于多方面的难题，鲜有对高焓流场参数测量的报道.文章介绍了利用激光诱导荧光（laser-induced fluorescence，LIF）技术对JF-10氢氧爆轰激波风洞产生的高焓实验气流温度的测量工作.搭建了用于脉冲式风洞的LIF测量系统，使用了NO分子作为荧光组分.因为高焓流场实验条件苛刻，本实验对传统的激光设置进行了调整，使用了平行于拍摄方向的竖直平面激光激发NO，使荧光信号更为集中，获得了清晰的LIF图像.利用双线测温法（two-line thermometry，TLT）测量高焓自由流中NO分子的转动温度，从而确定气流的平转温度.测量结果表明，JF-10实验气流的平转温度为600 K.      

FD-21风洞Ma=10高超声速推进试验技术探索

针对Mach数8以上（Ma>8）冲压发动机地面试验能力不足问题,基于FD-21高能脉冲风洞,开展了吸气式推进试验技术探索,提升了FD-21风洞的重活塞驱动能力,获得了总压18.66 MPa、总温3 950 K、Ma=9.62、静压436.6 Pa、速度3 km/s的高焓大动压模拟流场,同时发展了高时间分辨率吸收光谱测量技术和基于重模型自由飞原理的发动机推阻测量方法.在此基础上,设计了弯曲激波压缩二元发动机,构建了燃料在线供应与喷注控制、模型悬挂与瞬态释放及相关测量一体的试验系统,在所建立的Ma=9.62风洞模拟环境中进行了集成验证试验,定量测得了有/无氢气射流与空气/氮气超声速气流作用下二元发动机的壁面压力、吸收光谱峰值吸收率、轴向力等数据,并利用纹影观测到了进气道唇口与燃烧室部位的波系特征.多次试验所得的壁面压力、峰值吸收率、轴向力随时间变化曲线均存在2 ms以上的平台,表明二元发动机建立了准定常流动.冷热态及氮气对照组对应的壁面压力分布、峰值吸收率、轴向力等数据呈现出了明显不同,且二者规律近似一致,一方面说明所建立的模拟流场、燃烧诊断技术、发动机推阻测量技术是有效的,另一方面也表明二元发动机实现了点火燃烧、获得有效热功转换,为后续相关研究奠定了良好的基础.      

新建高焓激波风洞Ma=8飞行模拟条件的实现与超燃实验

针对高Mach数超燃冲压发动机实验能力空缺问题,基于航天十一院新建的FD-21高能脉冲风洞,进行了Ma=8超燃飞行条件的模拟能力设计与调试,获得了总焓2.9 MJ/kg、总压11.01 MPa实验条件,实现了Ma=8、高度31 km飞行条件的风洞模拟.在此基础上,研发了匹配的氢燃料供应及喷注时序控制系统,设计了超燃冲压发动机模型,开展了超燃冲压发动机模型自由射流应用性风洞实验,获得了氢气燃料与空气、氮气超声速气流耦合流动作用下的实验模型壁面压力数据.在当量比近似一致条件下,空气来流对应的燃烧室壁面压力明显高于氮气来流情况,表明氢气在1 ms有效实验时间内完成了与超声速空气来流的混合、点火与燃烧,获得燃烧释热特性,确认了在FD-21高能脉冲风洞开展高Mach数超燃实验是切实可行的,为后续研究奠定了良好的基础.      

JF12长实验时间激波风洞10°尖锥气动力实验研究

介绍了在中国科学院力学研究所JF12长实验时间激波风洞上开展的10°尖锥标模的天平测力实验研究结果.JF12激波风洞的实验时间为100~130 ms,名义Mach数为7.0,喷管出口直径为2.5 m,总焓为2.5 MJ/kg,复现了35 km高空的飞行条件.采用六分量应变天平,攻角分别为-5,0,5,10和14°,模型长度为1.5 m,质量为50 kg.实验结果表明,在100~130 ms的实验时间里,应变天平的输出信号含有3~4个完整周期,可以通过对天平的输出信号进行平均直接获得气动力/矩测量结果,而不再需要进行加速度补偿,且气动力系数重复测量的不确定度小于2%.JF12激波风洞气动力系数的测量结果与传统高超声速风洞的结果符合得较好,表明在2.5 MJ/kg的总焓下,真实气体效应对该模型气动力特性的影响不明显.      

激光诱导荧光技术在高焓空气氮原子测量中的应用

高超声速飞行器再入大气层时,受到激波的压缩和激波层内粘性阻滞作用,周围绕流流场的空气温度在4 000～15 000 K之间,使空气中的氧、氮分子发生离解,从而出现高温气体效应,形成高焓化学非平衡流。飞行器表面防热材料基本都含有大量的碳元素,通常情况下主要是氧原子与碳发生反应,但在焓值大于18 MJ·kg-1的情况下,氮原子与飞行器表面碳反应的无量纲烧蚀因子BC_N＞0.172 5,此时碳在高焓空气介质中的无量纲质量烧蚀因子BC_air＞0.345,因此,碳的氮化烧蚀变得非常剧烈,和氧化烧蚀相当;同时离解的氮原子也会在飞行器表面发生催化复合反应放出大量的热,使飞行器表面承受更多的热载荷。因此,分析高焓化学非平衡流流场中的氮原子具有现实意义。在地面模拟设备中建立高焓化学非平衡流场,对氮原子进行测量技术,可以很好的对其进行研究。双光子吸收激光诱导荧光（TALIF）技术作为一种非接触测量,在不干扰流场环境的情况下,可以直接获得氮原子的浓度分布。对流场氮原子激发荧光,通过布置在风洞试验段外与流场和激光形成的平面呈垂直方向的ICCD获取到二维氮原子的荧光信号。为确保荧光图像的清晰及视场合适,选择了Nikon f=50 mm F/1.4镜头作为前级收光设备。实验成像采用50次曝光的累计结果,以消除气流扰动及激光能量抖动造成的不确定性。实验中,在理论激发波长附件进行测试,优化选择出206.717 nm作为正式实验中脉冲激光的最佳激发波长。在最佳激光波长条件下,从小到大调整激发能量,获得了该环境下的氮原子激发的非饱和线性区为1.8 mJ以下。正式实验过程中激光能量为1.6 mJ,处于线性区。对所获取的荧光图像进行处理,提取激光中心线上的荧光强度进行分析,发现无论是亚声速还是超声速,荧光强度沿径向都呈驼峰状分布,与之前氧原子测试结果比较,发现流场中氮分子还未完全离解,这符合实验风洞流场特性。     

基于多模态PID的曳引机驱动控制系统设计

曳引机的驱动控制系统是垂直升降电梯的关键设备,对电梯性能具有重要影响,具有较大的研究价值。对一种基于多模态PID控制的永磁同步曳引机电梯驱动控制系统进行了研究。给出了曳引机驱动控制系统的总体设计方案,将系统分为主控模块、驱动模块和信号采集模块进行设计并介绍了各模块硬件电路的设计。针对曳引机控制采用了电流、速度双闭环控制算法,给出了主控制器DSP的软件流程设计,并对速度环采用的多模态PID控制算法进行了研究。在电梯公司的试验塔对设计的驱动控制系统进行现场调试,调试结果表明电梯在高、中、低速下都能够良好地跟踪给定的S型速度曲线,且超调量较小,稳态误差较小,可以满足电梯控制的性能指标要求。     

以高温燃气为试验介质的爆轰波风洞

为了满足高温燃气流动研究的需求,提出了一种新的实验装置——爆轰波风洞.该风洞基本原理是利用高压气体驱动爆轰波后高温气体,为其提供消除Taylor稀疏波的运动边界条件,使爆轰波后气流保持均匀恒定所需状态.在结构布置上,爆轰波风洞与激波风洞类似,因此很容易利用激波风洞实现爆轰波风洞的运行模式,但两者的流动过程和参数间关系有明显的区别.首先理论分析了爆轰风洞流动过程并得出参数间关系,而后据此开展了实验验证.理论和实验结果表明该装置可以产生多种类型、不同状态的高温燃气,并可实现对燃气状态的准确控制.该装置实验能力和应用范围还能进一步扩展.      

基于风洞的设备健康管理与数据有效性判定平台研究

低速增压风洞是满足我国航空工业科技发展而建设的一座气动力重大基础试验设施。为了保障该设施的高效率和可靠地运行,以各机电设备、电气测控设备、机械装置为对象,根据其故障模式和故障特点选取合适的监测点,获取实时工作状态数据,再以数据为基础,进行状态监测、故障诊断、故障预测,实现预先性决策和针对性快速维修。基于OSA-CBM 体系构建的风洞健康管理系统,根据设备的运行状态,实现对试验数据的有效性进行实时判定,并实现了风洞装备由事后维修向视情维修转变;实现了装备从使用、维护、管理模式由分散式管理向集约式管理的转变;实现了装备系统故障诊、预测及判读从人工智能向机器智能的转变。     

高超声速脉冲风洞模型自由飞试验技术

风洞模型自由飞试验利用高速相机记录自由飞行模型的运动历程, 再根据模型运动特征参数反演模型的气动特性.由于没有支撑系统的干扰, 该试验能够较真实地模拟飞行状态, 在飞行器静/动稳定特性研究中具有独特的优势.文章在JF-8A高超声速脉冲风洞中开展了10°尖锥模型自由飞试验, 并以圆球模型的自由飞运动测量风洞动压, 对模型运动特征参数的数字图像提取技术及气动参数的辨识方法等关键技术进行了研究.      

聚氨酯泡沫反向阴燃的数值模拟

本文根据两步反应机理,建立了2维非稳态燃料阴燃的数学模型.该模型考虑了气体在多孔介质内扩散系数的变化.应用该模型模拟了来流速度对阴燃速度及平均最高温度的影响,结果表明;首先阴燃传播速度随着来流速度的增大而增大,当风速为0.2 cm/s时,阴燃速度达到最大值0.0093 cm/s,而后随着风速的增大阴燃速度逐渐降低直至熄灭;来流速度对阴燃最高温度影响不大.同时还模拟了氧气浓度的影响、燃料阴燃中气体组分和固体成分的变化以及温度分布情况.     

多有源区隧道再生半导体激光器稳态热特性

 利用有限元软件ANSYS结合傅里叶定律,对制约适用于光纤耦合输出的新型高功率多有源区隧道再生半导体激光器长寿命工作的稳态热特性进行了系统计算、分析。获得了这种新型器件工作时各有源区温度分布特征及与传统单有源区器件稳态热特性的区别,并给出了多有源区隧道再生半导体激光器工作时各有源区温度的估算方法,同时对有效降低这种新型器件热阻的方法进行了讨论。结果表明:连续工作时,多有源区隧道再生半导体激光器比同材料体系传统结构器件更易获得较高的输出功率。     

金属烧结丝网在内场消声中的应用

利用试验手段研究暂冲式风洞稳定段内安装不同规格烧结金属丝网对风洞上游控制阀后气流噪声和湍流度抑制作用。试验结果表明:多层金属烧结丝网可在全频段内大幅度降低上游气流的噪声,最大可达21 dB;消声量与金属烧结丝网无量纲的压力损失系数成正比,压力降与金属烧结丝网层数呈现出非线性叠加的结果。另外发现烧结金属烧结丝网对气流速度脉动亦具有突出的抑制效果。例如,试验段马赫数Ma=1:5时,120目26层+160目26层组合烧结金属丝网出口气流速压脉动幅值减小为入口来流的18%,湍流度由11.7%降至3%。因此金属烧结丝网适合于暂冲式风洞的内场降噪。     

Design and performance of an open jet wind tunnel for aero-acoustic measurement

This paper presents the design and performance of an open jet, blow down wind tunnel that was newly commissioned in the anechoic chamber at the ISVR, University of Southampton, UK. This wind tunnel is intended for the measurement of airfoil trailing edge self-noise but can be extended to other aeroacoustic applications. With the primary objectives of achieving acoustically quiet and low turbulence air jet up to 120 m/s through a 0.15 m × 0.45 m nozzle, several novel noise and flow control techniques were implemented in the design. Both the acoustical and aerodynamic performances of the open jet wind tunnel were examined in detail after its fabrication. It is found that the background noise of the facility is adequately low for a wide range of exit jet velocity. The potential core of the free jet is characterized by a low turbulence level of about 0.1%. Benchmark tests by submerging a NACA0012 airfoil with tripped and untripped boundary layers at 0° and 10° angles of attack respectively into the potential core of the free jet were carried out. It was confirmed that the radiating airfoil trailing edge self-noise has levels significantly above the rig noise over a wide range of frequencies. The low noise and low turbulence characteristics of this open jet wind tunnel are comparable to the best facilities in the world, and for its size it is believed to be the first of its kind in the UK.     

Design and performance of a small-scale aeroacoustic wind tunnel

The D5 aeroacoustic wind tunnel at Beihang University is a newly commissioned small-scale closed-circuit wind tunnel with low turbulence intensity and low background noise. The wind tunnel is built to study both aerodynamic and aeroacoustic performance of aircraft components or scaled models. The wind tunnel has two types of test sections, the closed type test section is used for aerodynamic tests while the open type test section is mainly used for aeroacoustic experiments. Both types of test section are 1 m in height and 1 m in width, and the maximum wind velocity in the test section can be up to 80 m/s. An anechoic chamber is built surrounding the test section to provide the non-reflecting condition. This paper provides an overview of design criteria and performance of the small-scale wind tunnel. The layout of the wind tunnel and some critical design treatments to improve aerodynamic and acoustic performance are discussed in detail. Some experiments are conducted to verify the performance of D5 wind tunnel, results confirm that the turbulence intensity is less than 0.08% in the core of test section and the background noise is comparable with other aeroacoustic wind tunnels. A scaled simplified nose landing gear model is also measured as a benchmark test, results reveal that noise radiated from the model is adequately higher than the background noise for a wide frequency range and remarkably consistent with other results from literatures.     

Characteristics of helium DC plasma jets at atmospheric pressure with multiple cathodes

A novel DC plasma torch with multiple cathodes is developed for generating laminar, transitional and turbulent plasma jets. The jet's characteristics, including jet appearance, voltage fluctuation, thermal efficiency, specific enthalpy, and distributions of temperature, pressure, and velocity, are experimentally investigated. The results show that as the gas flow rate increases, the plasma jet transforms first from the laminar state to the transitional state and second to the turbulent state. Compared with the transitional/turbulent jet, the laminar jet possesses not only a better stability and a longer hightemperature zone but also a higher average/core temperature and a higher specific enthalpy at the nozzle's outlet. With the change of jet states from the laminar to the turbulent flow, the core pressure and velocity at the nozzle's outlet increase,while the decaying rates of temperature/pressure/velocity along the jet's axial direction increase sharply. Furthermore, applications of laminar, transitional and turbulent jets for zirconia spray coating are described. The test results indicate that the long laminar jet is favorable for the deposition of a high-quality coating because the powder particles injected into the laminar jet may have better heating and lower kinetic energy.     

Thermal expansion and lattice dynamics under pressure of ZnS,ZnSe and ZnTe

The thermal expansion against temperature of ZnS, ZnSe and ZnTe is studied theoretically using the experimental pressure dependence of elastic stiffness constants and phonon frequencies. The mode Grüneisen parameters obtained from the high pressure effect on the one- and two- phonon Raman spectra at the metallic transition pressure by Weinstein are used originally, but do not reproduce the experimental linear expansion coefficient at high temperatures. The contributions from optical modes with large phonon frequency are important to the thermal expansion at high temperatures, and a set of mode Grüneisen parameters, which bring good agreement with the observed linear expansion coefficient not only at low temperatures, but also at high temperatures, are obtained. Then, the phonon dispersion curves of ZnS, ZnSe and ZnTe at their metallic transition pressures are quantitatively shown.     

Acoustic near-field characteristics of a conical,premixed flame

The occurrence of self-excited pressure oscillations routinely plagues the development of combustion systems. These oscillations are often driven by interactions between the flame and acoustic perturbations. This study was performed to characterize the structure of the acoustic field in the near field of the flame and the manner in which it is influenced by oscillation frequency, combustor geometry, flame length and temperature ratio. The results of these calculations indicate that the acoustic velocity has primarily one- and two-dimensional features near the flame tip and base, respectively. The magnitude of the radial velocity components increases with temperature ratio across the flame, while their axial extent increases with frequency. However, the acoustic pressure has primarily one-dimensional characteristics. They also show that the acoustic field structure exhibits only moderate dependencies upon area expansion and flame temperature ratio for values typical of practical systems. Finally, they show that the local characteristics of the acoustic field, as well as the overall plane-wave reflection coefficient, exhibit a decreasing dependence upon the flame length as the area expansion ratio increases.     

采用3S分离器的天然气液化过程的参数分析

采用低温下3S分离器的一维稳定流动数学模型,对影响采用3S分离器的天然气液化过程的主要参数——入口压力、温度、组分以及膨胀后的压力进行了分析。结果表明,存在一从低压低温到高压高温的"脊形"区域,在此范围内3S分离器具有明显的优势。3S分离器对天然气组分的变化不敏感。膨胀后压力越低,天然气的液化率越高。     

高超声速条件下7°直圆锥边界层转捩实验研究

在Ma=6低噪声风洞中开展了半锥角7?的直圆锥边界层转捩相关实验研究.利用响应频率达到MHz量级的高频压力传感器对圆锥壁面脉动压力进行了测量,研究了高超声速圆锥边界层中扰动波的发展过程.结果表明:高超声速圆锥边界层中第二模态扰动波产生的位置以及扰动波特征频率和波长等参数受雷诺数影响较大,当单位雷诺数从2×106m~(-1)增加到8×106m~(-1)时,第二模态波的特征频率从55 k Hz增加到226 k Hz;随着单位雷诺数增加,边界层中扰动增长速度加快,第二模态波出现在圆锥表面更靠近上游的位置;相同单位雷诺数条件下,随着第二模态波的向下游传播,其特征频率逐渐减小.通过对比发现自由来流湍流度对边界层中扰动波的发展同样有较大影响,自由来流湍流度降低,边界层中的第二模态波的特征频率明显减小.利用互相关分析得出第二模态扰动波在边界层中的传播速度大约为当地主流速度的0.8—0.9倍.在1?小攻角条件下,圆锥迎风面和背风面边界层发展呈现出明显的差异,背风面边界层中扰动发展提前,第二模态波出现在更靠近上游的位置,而迎风面中扰动发展受到抑制,第二模态波特征频率更大.     

Observation of high-field-side crash and heat transfer during sawtooth oscillation in magnetically confined plasmas

High resolution (temporal and spatial), two-dimensional images of electron temperature fluctuations during sawtooth oscillations were employed to study the crash process and heat transfer in magnetically confined toroidal plasmas. The combination of kink and local pressure driven instabilities leads to a small poloidally localized puncture in the magnetic surface at both the low and the high field sides of the poloidal plane. This observation closely resembles the "fingering event" of the ballooning mode model with the high- mode only predicted at the low field side.