折射式激光多普勒测速系统

为了测量透明物体横向运动时的位移速度,提出了一套基于激光外差干涉技术的折射式激光多普勒测速系统,并对该系统所采用的多普勒效应测速方法进行了研究。首先,通过外差干涉系统使测量光与参考光发生干涉,利用信号探测系统探测它们合光束光强变化波形。然后,使用信号分析软件分析此波形,得到合光束的拍频,即测量光与参考光的频率之差。最终,利用此拍频值进行理论计算,求出垂直于探测光方向匀速运动时三棱镜样品的位移速度,并分析了整个系统的测量误差。实验结果表明,对20μm/s、80μm/s、140μm/s、200μm/s等给定的位移速度,该系统的速度测量误差不超过1.5%。测量结果具有良好的可重复性,证实了该系统的有效性与可靠性。实验系统原理简单,输出信号信噪比较高,测量精度高,具有广泛的适用性。     

X光转换靶区物理现象研究

描述了束靶作用产生X光的同时伴随有回流离子、回流颗粒的产生及对加速器品质的影响;利用激光干涉法测量等离子体(回流离子)的性能参数,得到靶前等离子体的密度为1022/m3;利用高速分幅相机测量回流颗粒运动速度为2～4km/s,根据该结果,设计3种快门阻挡回流颗粒;最后给出多脉冲下X光转换靶的物理设计,即泡沫靶和叠靶(复合靶)。     

脉冲激光与正激波相互作用过程和减阻机理的实验研究

纳秒脉冲激光具有峰值功率密度高、易于击穿空气形成等离子体这一突出优势,在降低超声速波阻方面具有重要应用价值.以深刻揭示减阻机理为目的,针对激光与正激波相互作用这一基本物理现象开展实验研究.发展高精度纹影技术以测量复杂激波结构,时间分辨率达到30 ns,空间分辨率达到1 mm;搭建快速PIV实验系统以定量测量流场速度和涡量,时间分辨率达到500 ns.探明了激光等离子体引致的球面激波和高温低密度区域特性,揭示了激光等离子体在正激波冲击下的流动特性与演化规律,并结合数值模拟结果阐明了脉冲激光等离子体降低超声速波阻的根本原因.研究表明:激光等离子体引致激波的初始马赫数随着激光能量而增大,形状由水滴形逐渐发展为球面形,传播速度随着时间降低,在50μs后接近于声速;高温低密度区域初始近似于球形,而后从激光入射方向的下游开始失稳,形成尖刺结构;在正激波冲击下,高温低密度区域演化为上下对称的双涡环结构,尺寸随着激光能量而增大.涡的卷吸和逆流可改变飞行器头部激波结构,是流场重构的重要形式,引起飞行器表面压力的大幅降低,是引起超声速飞行器波阻降低的重要机理.     

聚龙一号上磁驱动铝飞片发射实验的数值分析与再设计

聚龙一号上PTS-151发次实验中,磁驱动加速370 μm厚飞片测得的最大速度为18 km/s,磁驱动加速482 μm厚飞片测得的最大速度为19 km/s。采用MDSC2程序, 对PTS-151发次实验进行了数值分析,结果表明:PTS-151发次实验中测量的最大速度的含义不同于以往文献中飞片的最大速度。以往文献中发射飞片在测试过程中自由面未被烧蚀,测试的最大速度为飞片自由面速度;PTS-151发次实验中两个飞片在测量过程中自由面被烧蚀,实验测量的最大速度为飞片被完全烧蚀前的一瞬间飞片内部最后一个固体面的速度。在飞片自由面未被烧蚀之前,370 μm厚飞片的计算最大自由面速度仅为7 km/s,482 μm厚飞片的计算最大自由面速度仅为11.8 km/s,远低于测量值。对PTS-151发次实验条件下飞片尺寸进行了再设计,飞片厚度为680 μm时最优,既能保证自由面未烧蚀,又使得飞片的速度最大,达到17.5 km/s。     

测量低密度气流速度和运动激波马赫数的火花放电法

本文在讨论了各种测量气流速度的方法,特别是Miller的放电法基础上,提出了一种测量低密度流场气流速度和运动激波马赫数的改进方法。本方法采用双曝光技术,有助于提高测量精度;在结构上和电路上的改进,克服了低密度流场中漏电问题。该方法适用于气流速度1200m/s以上,密度约0.05kg/cm~3的高速瞬态流场中的气流速度和运动激波马赫数的测量。     

脉冲激光等离子体与正激波相互作用的PIV实验研究

脉冲激光等离子体与超声速流场相互作用在飞行器减阻隔热、点火助燃等方面具有重要的应用价值.纹影实验方法只能定性或半定量地反映流动状态.为定量研究速度分布和旋涡结构,针对激光等离子体及其与正激波相互作用过程开展粒子图像测速PIV实验研究.在激波管实验平台上建立了纳秒脉冲激光能量沉积系统和PIV测量系统,通过定量测量,探明了激光等离子体引致的激光空气泡以及热核的流动特性,揭示了激光等离子体在正激波冲击下的流动特性与演化规律,并给出了激光能量大小和位置对相互作用过程的影响.结果表明:激光空气泡内的速度分布在激光入射方向上并不关于击穿点对称,而是在靠近激光入射方向一侧的流速略大于远离激光入射方向一侧;斜压导致热核在演化初期产生涡环,后期则由剪切主导;正激波与激光空气泡界面、热核界面相互作用时,产生斜压涡量,当激光能量为87.8 mJ、正激波马赫数1.4时,热核在正激波作用下产生的涡量比在静止空气中演化时大1个数量级;激光与正激波相互作用的关键过程是热核在正激波冲击下演化成涡环,在激波波前注入激光能量能够获得更加显著的涡环.     

INS/Doppler/GPS组合导航系统中航向误差的辨识

提出了一种INS/Doppler/GPS组合导航系统中航向误差的辨识方法.经过坐标转换得到的Doppler速度中包含了惯导系统航向误差的影响,可以考虑以GPS速度为基准信息,从Doppler速度中解算航向误差.但由于速度噪声的影响,这样得到的航向误差带有大量噪声.该方法用一个以时间为变元的多项式来逼近航向误差,以解算出的航向误差作为观测量,采用递推最小二乘法辨识出该多项式的各次项系数,进而计算出航向误差,达到滤除观测噪声的效果.仿真试验表明,在GPS速度噪声标准差为0.1 m/s、Doppler速度噪声标准差为0.5 m/s的情况下,航向误差的辨识精度优于0.22(2σ),收敛时间不超过120s.     

火箭橇加载试验技术研究

根据空气动力学和火箭发动机的相关理论,针对600 m长无缝滑车轨道,对搭载50 kg有效载荷、速度为45 m/s和搭载100 kg有效载荷、速度为200 m/s的两种双轨滑车进行了理论估算和试验验证。试验中,滑车的速度测试采用磁感应法、激光法和高速摄影法三种方法。试验结果表明,三种测试方法获得的滑车速度值一致,测试结果与理论计算值符合得较好。     

脉冲激光与正激波相互作用过程和减阻机理的实验研究

纳秒脉冲激光具有峰值功率密度高、易于击穿空气形成等离子体这一突出优势,在降低超声速波阻方面具有重要应用价值.以深刻揭示减阻机理为目的,针对激光与正激波相互作用这一基本物理现象开展实验研究.发展高精度纹影技术以测量复杂激波结构,时间分辨率达到 30ns,空间分辨率达到 1mm;搭建快速~PIV 实验系统以定量测量流场速度和涡量,时间分辨率达到 500ns.探明了激光等离子体引致的球面激波和高温低密度区域特性,揭示了激光等离子体在正激波冲击下的流动特性与演化规律,并结合数值模拟结果阐明了脉冲激光等离子体降低超声速波阻的根本原因.研究表明:激光等离子体引致激波的初始马赫数随着激光能量而增大,形状由水滴形逐渐发展为球面形,传播速度随着时间降低,在50$\mu$s 后接近于声速;高温低密度区域初始近似于球形,而后从激光入射方向的下游开始失稳,形成尖刺结构;在正激波冲击下,高温低密度区域演化为上下对称的双涡环结构,尺寸随着激光能量而增大.涡的卷吸和逆流可改变飞行器头部激波结构,是流场重构的重要形式,引起飞行器表面压力的大幅降低,是引起超声速飞行器波阻降低的重要机理.      

光纤位移干涉仪在爆轰加载飞片速度测量中的应用

利用光学多普勒效应和外差方法搭建了一台光纤位移干涉仪。装置采用光通信行业中已经发展成熟的器件,主要由带尾纤的半导体激光器、三端口环形器、光纤探头、宽带探测器以及宽带高采样率示波器等构成。整个装置结构简单,价格便宜,采用了信号光和参考光同轴结构,实现了任意反射面的速度测量,克服了偏振模式色散的影响,能够实现长量程测量,量程达到20 mm。利用该装置进行了爆轰加载下飞片速度测量,测量最高速度达到1 300 m/s,工作距离达到20 mm,同时利用VISAR对飞片速度进行了对比测量,结果表明用两种不同方法所测得的速度曲线吻合很好。     

The possibility of measuring turbulence by a correlation method

In [1] a correlation method for measuring the velocity pulsations in stationary plasma flows was described. The magnitude of the pulsations was determined from the value of the frequency deviation in the spectrum of the cross-correlation functions of optical fluctuations at two closely arranged points along the flow.In the present work, an attempt is made to justify such a method for measuring the characteristics of turbulence both in plasma and in any low-temperature gas flows.     

考虑气体压缩性的多孔材料渗透率和惯性系数的测定

多孔介质材料的渗透率和惯性系数是决定多孔介质中流体流动特性的重要参数，一般需要通过实验进行测定，在测定渗透律和惯性系数量，选用气体作为工作介质可以为实验带来极大的方便，然而通常的实验都将气体看作不可压缩流体，直接根据Darcy-Forchheimer定律得到这两个参数，这种近似对实验条件如样品厚度、工作压力等提出了很多要求，本文提出了在考虑气体压缩性的情况下测定渗透率和惯性系数的方法，该方法可以大大降低实验时对样品厚度、工作压力等条件的要求。本文还根据该方法对多孔材料PVF进行了渗透率和惯性系数的测定，并对测量结果进行了验证。     

Principles of flow field diagnostics by laser induced biacetyl phosphorescence

A new method for measuring the density, temperature and velocity of N₂ gas flow by laser induced biacetyl phosphorescence is proposed. The characteristics of the laser induced phosphorescence of biacetyl mixed with N₂ are investigated both in static gas and in one-dimensional flow along a pipe with constant cross section. The theoretical and experimental investigations show that the temperature and density of N₂ gas flow could be measured by observing the phosphorescence lifetime and initial intensity of biacetyl triplet (³A_u) respectively. The velocity could be measured by observing the time-of-flight of the phosphorescent gas after pulsed laser excitation. The prospect of this method is also discussed.     

等离子体激励气动力学探索与展望

等离子体激励气动力学是研究等离子体激励与流动相互作用下, 绕流物体受力和流动特性以及管道内部流动规律的科学, 属于空气动力学、气体动力学与等离子体动力学交叉前沿领域. 等离子体激励是等离子体在电磁场力作用下运动或气体放电产生的压力、温度、物性变化, 对气流施加的一种可控扰动. 局域、非定常等离子体激励作用下, 气流运动状态会发生显著变化, 进而实现气动性能的提升. 国际上对介质阻挡放电等离子体激励、等离子体合成射流激励及其调控附面层、分离流动、含激波流动等开展了大量研究. 等离子体激励调控气流呈现显著的频率耦合效应, 等离子体冲击流动控制是提升调控效果的重要途径. 发展高效能等离子体激励方法, 通过等离子体激励与气流耦合, 激发和利用气流不稳定性, 揭示耦合机理、提升调控效果, 是等离子体激励气动力学未来的发展方向.      

爆轰驱动惰性气体磁流体发电试验研究

磁流体发电装置作为一种特殊的高功率脉冲电源,具有效率高、容量大、启动快的优点,制约其发展的关键在于如何获得高电导率的发电工质.爆轰驱动具有远超常规方式的驱动能力,在提供高温、高电导率气体方面独具优势.将爆轰驱动激波管技术应用于磁流体发电,有利于突破磁流体发电技术瓶颈,故据此开展了基于爆轰驱动激波管技术的惰性气体磁流体发电试验研究.爆轰驱动根据激波管点火位置不同分为反向和正向两种运行模式,反向爆轰驱动可提供时间较长、状态稳定的试验气流,而正向爆轰优势在于产生高焓试验气流.试验系统由爆轰驱动激波管、拉瓦尔喷管、发电通道、电磁铁和真空罐等组成,试验中分别以反向爆轰和正向爆轰驱动激波管产生发电工质,利用激波将惰性气体压缩至高温从而发生电离,形成的等离子体经喷管加速后,最终在法拉第直线型发电机内切割磁感线输出电能.磁场强度0.9 T的条件下,反向爆轰在负载3.5Ω时获得了较稳定的1.9 kW输出功率,持续时间1.5 ms;外接35 mΩ负载时,正向爆轰在0.3 ms内短时输出功率高达212 k W,功率密度为0.2 GW/m³.试验成功验证了基于爆轰驱动激波管技术的惰性气体...     

A self-similar solution of exponential shock waves in non-ideal magnetogasdynamics

A self similar method is used to analyze numerically the one-dimensional, unsteady flow of a strong cylindrical shock wave driven by a piston moving with time according to an exponential law in a plasma of constant density. The plasma is assumed to be a non-ideal gas with infinite electrical conductivity permeated by an axial magnetic field. Numerical solutions in the region between the shock and the piston are presented for the cases of adiabatic and isothermal flow. The general behaviour of density, velocity, and pressure profiles remains unaffected due to presence of magnetic field in non-ideal gas. However, there is a decrease in values of density, velocity and pressure in case of magnetogasdynamics as compared to non-magnetic case. It may be noted that the effect of magnetic field on the flow pattern is more significant in case of isothermal flow as compared to adiabatic flow. The effect of non-idealness, specific heat exponent and magnetic field strength on the variation of shock strength across the shock front is also investigated.     

NUMERICAL SIMULATION OF A FLOW IN A SENSOR FOR MEASURING THE FLOW STAGNATION TEMPERATURE IN IMPULSE WIND TUNNELS

Journal of Applied Mechanics and Technical Physics - This paper describes a problem of measuring a gas flow temperature using thermocouples for which the time it takes to reach an equilibrium...     

Low Pressure Gas Percolation Characteristic in Ultra-low Permeability Porous Media

Low pressure gas percolation characteristic in ultra-low permeability porous media is investigated in this article through core flow experiments. The results show that the wall-slip layer covers more than 10% of the average porous channel radius on account of minimum pore size when the permeability is below 0.1 × 10^?3μ m ² order, and seepage behavior is contrasted to that in mid-high permeability pore media. When the gas pressure is not high enough, the flow regime turns into transitional flow instead of slip flow, and nonlinear relationship between the measured gas permeability and the reciprocal of average pressure exists. The gas measuring permeability experiment would be influenced by the non-linear relationship. If Klinkenberg-corrected method is applied to speculate the equivalent liquid permeability, the extrapolated value will become less or minus. Simultaneously, actual gas flow velocity at the outlet is beyond the calculated value with Klinkenberg formula. A new gas seepage model based on the general slip boundary condition is derived from the homogenization technique in this article. At last the flow model is examined to be suitable for representing the gas flow behavior in ultra-low permeability media and estimating the absolute permeability from single-point, steady-states measurements.     

Dynamic film thickness between bubbles and wall in a narrow channel

The present paper describes a novel technique to characterize the behavior of the liquid film between gas bubbles and the wall in a narrow channel. The method is based on the electrical conductance. Two liquid film sensors are installed on both opposite walls in a narrow rectangular channel. The liquid film thickness underneath the gas bubbles is recorded by the first sensor, while the void fraction information is obtained by measuring the conductance between the pair of opposite sensors. Both measurements are taken on a large two-dimensional domain and with a high speed. This makes it possible to obtain the two-dimensional distribution of the dynamic liquid film between the bubbles and the wall. In this study, this method was applied to an air–water flow ranging from bubbly to churn regimes in the narrow channel with a gap width of 1.5 mm.     

Use of hot-wire anemometry for measuring the nanopowder flow velocity

A new technique for measuring the flow velocity of nano-scale powders is used. The hot-wire anemometry method widely used in gas flows is employed for investigating nanopowder flows. By way of illustration, the flows of nanopowders of aluminum oxide C and silicon dioxide aerosil A-90 and A-380 in a vertical channel are studied. The results obtained show that nanoscale powder flow investigation by means of the hot-wire anemometry is promising.