Aero-optical wavefront measurement technique based on BOS and its applications

A collimated light beam will be refracted if it propagates through a flow-field with index-of-refraction variations,and its wavefront will be distorted.If we measure the deflection angle of the light beam,the gradient of the wavefront can be obtained using the Malus law,and the wavefront aberration can be computed with a reconstruction algorithm.Two characteristics of background oriented schlieren(BOS) are conducive to wavefront aberration measurement:BOS can be used to measure the deflection angle of a light beam by measuring the displacement field between the reference image and the experiment image.Moreover,in a BOS system of Schlieren mode,only the ray perpendicular to the background image can be captured with a camera.This is helpful to measure wavefront aberrations that occur after a planar wavefront has passed through the flow-field.Based on these characteristics of BOS of Schlieren mode,a new wavefront measurement technique,which is called the BOS-based wavefront technique(BOS-WT),is proposed in this paper.It works by constructing the relationship between the displacement of the background image and the aero-optical wavefront gradient and uses the Southwell wavefront reconstruction algorithm.A BOS-WT system was assembled,and its temporal resolution was found to be 6 ns,and its temporal-correlation resolution reached 0.2 μs.A BOS-WT can measure the time-correlation transient wavefront quantitatively.It is simple and easy to operate.In this paper,we also present a study of the aero-optical performance of supersonic mixing layer based on our BOS-WT transient wavefronts at an interval of 5 μs.The results showed the wavefront was transient and distorted after it had passed through the mixing layer.Through the analysis of the data at the 5 μs interval,the temporal evolution of wavefront can be obtained.     

Optical wavefront distortion due to supersonic flow fields

The optical wavefront distortion caused by a supersonic flow field around a half model of blunt nose cone was studied in a wind tunnel. A Shack-Hartmann wavefront sensor was used to measure the distorted optical wavefront. Interesting optical parameters including the peak variation (PV), root of mean square (RMS) and Strehl ratio were obtained under different test conditions during the experiment. During the establishing process of the flow field in the wind tunnel test section, the wavefront shape was unstable. However after the flow field reached the steady flow state, the wavefront shape kept stable, and the relative error of wavefront aberration was found small. The Shack-Hartmann wavefront sensor developed was proved to be credible in measuring quantitatively the optical phase change of light traveling through the flow field around model window.     

An experimental study on fine structures of supersonic laminar/turbulent flow over a backward-facing step based on NPLS

Fine structures of supersonic flow over a 5 mm high backward facing step(BFS),including expansion wave fan,reattachment shock,supersonic boundary layer were measured in a Ma=3.0 low-noise indraft wind tunnel.By varying the superficial roughness of the wall upstream from the step,supersonic laminar flow and supersonic turbulent flow could be formed over a BFS.Measurements on the spatiotemporal features of the holistic flow field and the fine structures in four typical regions were carried out using NPLS(nano-based planar laser scattering).Flow structures,including expansion wave fan,reattachment shock,supersonic boundary layer and its separation,reattachment and redevelopment are revealed by measuring the holistic structure of the transient flow field.Comparing the two time-averaged flow fields with each other,it is apparent that supersonic turbulent flow over a BFS(STF-BFS) has a larger expansion angle and a shorter recirculation region,and its redeveloped boundary layer increases at a smaller obliquity while the angle of reattachment shock is the same for the supersonic laminar flow over a BFS(SLF-BFS).With regard to time-evolution features,the K-H vortices in the SLF-BFS suffers from shearing,expansion,reattachment and three-dimensional effects while in the STF-BFS large-scale structures are affected by the incline and distortion at the reattachment point due to expansion,viscosity and reverse-pressure.Studies on local regions indicate that in the SLF-BFS,the emergence of compression waves which distinctly converge into a reattachment shock is due to the local convective Mach number and the inducement of K-H vortices in the free shear layer.Nevertheless,in the STF-BFS,compression waves and K-H vortices are barely evident,and the formation of a reattachment shock is related to the wall compressive effect.     

探头式电磁流量计的理论研究和样机试验

本文分析了探头式电磁流量计的基本原理。根据电磁学和流体力学的理论求得了圆柱二电极、圆柱四电极、椭圆柱以及流线型柱体探头感应电动势的解析解。文中还讨论了边界层绕流圆柱探头和有限区间对探头输出信号的影响。从理论解可以看出,探头电极间的感应电动势与来流速度之间呈明显的线性关系。此外,文中还推荐了几种延迟或避免探头表面发生边界层分离的方法。对于圆柱和椭圆柱样机的实验证实了理论分析的结果。     

不同飞行高度下超声速来流/射流及其相互作用的数值模拟

采用高精度格式求解二维Navier-Stokes方程,研究了不同飞行高度下超声速来流和射流在后台阶相互作用的流场基本结构.时间推进采用三阶精度Runge-Kutta格式,分别应用五阶精度加权本质无振荡(weighted essentially non-oscillatory,WENO)格式、六阶精度中心差分格式来离散对...     

基于Hartmann-Shack波前传感器的实时人眼像差测量

为实时、准确地测量人眼的像差,保证人眼像差校正时数据的准确性,依据Hartmann-Shack波前传感器测量像差探测原理,设计搭建了一套基于Hartmann-Shack波前传感器的人眼像差实时测量系统。用该系统对人眼的动态像差进行了测量实验,对实验的结果进行了分析。实验结果表明:为了满足传感器获取光斑图及保证人眼的安全,入瞳的激光功率80μW较为合适;像差测量的结果折算成屈光度与主观方法验光值结果基本相符;动态像差连续测量观察像差波动的时间约在0.2~0.5 s,与人眼的波前像差变化频率在5 Hz左右的结论基本相符。结果表明该系统满足了人眼像差测量的可行性和准确性要求。     

象差波面光束内部干涉的研究

运用惠更斯原理分析了象差波面传播变形和内部干涉的现象,提出了由原始波面求得新波面的计算方法,并以此方法计算了球差波面的传播过程中的波面演化,揭示了象差波面内部干涉的内在机理.     

Experimental investigation on upstream-injection interaction with a scramjet cavity flameholder

The study has evaluated the coherent structures and the velocity field of gaseous transverse jet upstream of a scramjet flameholder in a supersonic turbulent flow. The high spatiotemporal resolution coherent structures of the jet plume/wakes and the cavity shear layer were obtained by utilizing the nanoparticle-based planar laser scattering technique. Compared to the no upstream injection case, the cavity shear layer downstream of the jet shows significant mass exchange with mainstream. The particle image veloc- imetry velocity field and the velocity profiles demonstrated that the interaction intensity of the cavity shear layer with the upstream injection is further enhanced as the injection stagnation pressure increases.     

波前像差引导的激光眼屈光手术中角膜切削模型

基于改变角膜厚度可以改变眼屈光系统波前像差的原理,提出了一种矫正眼波前像差的角膜切削模型．首先给出理想参考平面波前和实际波前之间的位置关系,用一个通用的数学模型表示了波前像差;其次用Zernike多项式系列来描述眼像差结构,将波前像差表示成带权重的Zernike多项式系列累加和的形式;最后将眼波前像差转换为光程差的形式,用光程差表示了角膜切削厚度。并进一步得出角膜切削厚度同波前像差之间转换的数学模型(像差矫正模型)．该像差矫正模型在理论上能矫正包括低阶像差(近视、远视、散光)和高阶像差在内的35项像差．     

火箭推力偏心特性研究

该文应用巴特勒提出的五面体双特征曲线网格方法对火箭喷管扩张段内的非定常非对称流场进行了数值模拟,获得了锥形喷管侧向推力随时间的变化曲线。分析表明,该文计算的侧向推力结果与定常状态下的数据是吻合的。证明五面体双特征曲线网格方法可用来研究非定常流动条件下的推力偏心特性。     

超音速风洞扩压器激波串现象的数值模拟

超音速扩压器性能研究具有非常重要的工程实际应用价值。该文为加深对超音速风洞扩压器内流场结构的理解,采用Fluent软件对“收缩段等直段扩张段”型扩压器流场进行了数值计算,较好模拟了扩压器中由激波/边界层干扰诱导的复杂流场的流场特性,再现了流场中的“激波串”和“伪激波”现象,与文献结果吻合较好。并以比较精细的二维网格计算结果对激波串的形成机理和典型流动结构进行了分析,同时应用于实际工程,对某超音速风洞扩压器不同二喉道长度状态下的扩压效率进行了比较。     

二维机翼非定常气动反命题的欧拉解法

提出在映象坐标下求解二维非定常欧拉方程获取二维振荡机翼的气动反命题解,给出了非定常气动反问题的边界条件和求解方法．该方法克服了以往基于势函数方程解反命题的局限,统一了亚音、跨音与超音流反问题的解法,并避免了非定常尾涡面的直接求解与反问题未知边界的不确定性．     

理想气体条件下平行圆盘止推气体轴承承载力特性研究

在高供气压力和大间隙下,平行圆盘止推气体轴承间隙中呈现出超音速主流区与边界层的复杂作用而导致高度复杂的流场。为探讨超音速主流区的特性,采用绝热理想气体和简化轴承模型分析环境背压不变时气膜间隙中流动状态与供气总压的依赖关系,推导出以供气总压和马赫数为主要变量的不同流态下轴承承载力的计算公式。结果表明,随着供气总压的变化,间隙内可能出现4种不同的流动状态,具体由供气总压与3个特征滞止压强的比值来决定;3个特征滞止压强与出口背压的比值仅取决于圆盘的内外半径比。当供气总压在环境背压和第2特征滞止压强之间时,随着供气总压的增大,轴承承载力从0降至最低负值;当供气总压大于第2特征滞止压强时,轴承承载力随着供气总压的提高而线性增大。     

源造波法在三维完全非线性数值波浪水槽中的应用

为消除波浪在水槽出流边界的反射及波浪遇到结构物后在入射边界形成的二次反射,基于时域高阶边界元方法建立三维完全非线性数值波浪水槽模型:利用源造波法产生入射波浪,采用人工阻尼层技术消除波浪反射及二次反射;建立水槽的格林函数并应用于整个计算域,消除水槽两侧壁和底面的积分,减少了计算量.利用所建模型分别对规则波和不规则波的数值实验表明,数值结果与理论解吻合良好,且在出流边界和入射边界均无反射现象.     

丘陵沟壑区域大场域空间流场模型边界效应和建模方法： 以山西运城某地区为例

基于计算流体力学相关理论,实现丘陵沟壑区域大场域空间内塔线高度层气流场的精准模拟是研究风载荷下高压输电线路风振响应及力学特性,实现塔-线偶联结构体优化设计的关键。但由于缺乏针对边界效应的系统研究,致使流场仿真结果不精准或模型边界过度冗余而难以求解。为了解决这个难题,论文基于数字高程模型（digital elevation model, DEM）数据对某典型地域建模,通过流场仿真和边界效应分析,系统讨论了复杂地形下特定高度层流场仿真中建模方法和边界效应的影响。结果表明: 计算域高度达到地形高差7倍以上时其边界效应影响基本消失;壁面边界约束导致的流场畸变随冗余距离增加而减小,选择700米的冗余距离可获得更稳定的风场。相关结论明确了计算域对于流场的影响以及流体模型边界效应的消除方法,对高压输电线路结构稳定性和抗风能力提升具有参考价值。     

水下铁磁性腔体外部感应磁场研究

在水下铁磁性腔体上测量地磁场必须消除干扰磁场的影响,其中感应磁场是干扰磁场的主要组成部分,它随着腔体方位的变化而变化。分析腔体感应磁场的有限元计算方法,建立二维、三维数学模型,重点是采用有限元积分法添加了Neumann边界条件,得到了腔体感应磁场方程。通过将二维模型的解析解与数值解相比对,验证了二维和三维感应磁场方程的正确性,从而运用数值计算方法得到腔体位置、姿态变化时感应磁场的分布。     

舰船平面磁场的边界矢量积分延拓方法

根据矢量格林恒等式,得到了大平面边界上各点磁场的矢量积分关系,进而找到了大平面内测量磁场和未知磁场的积分关系,通过边界剖分离散化形成线性方程组,求解得到未知磁场,达到磁场延拓的目的.延拓得到的大平面磁场能够提高远场磁场的计算精度.实验算例证明了该延拓方法的有效性,表明利用该方法能够较准确地由小范围测量磁场延拓得到大平面...     

沿圆弧形路径积分的反射式超声层析成像方法及实验研究

讨论了近场及远场条件下沿圆弧积分的超声反射ＣＴ成像的重建算法,进行了计算机模拟成像,在此基础上,建立了一套超声反射ＣＴ成像系统,对部分样品模型进行了实验成像。     

正交各向异性涂层结构温度场计算

边界积分方程中的几乎奇异积分计算难题阻碍了边界元法在涂层结构中的应用．针对此,给出了正交各向异性温度场边界元法中几乎奇异积分的正则化算法,并将其应用于分析涂层结构的温度场．首先计算了涂层和基体为同种材料时涂层结构内的温度场,并与精确解比较来验证该方法的正确性,然后计算了涂层和基体为不同材料时正交各向异性涂层结构内的温度场．数值算例表明,同常规边界元法比较,该方法可以计算更薄涂层内的温度场．     

电磁消涡与减震技术研究

利用流体边界层上的电磁体积力控制流体边界层的周期性脱落与分离,限制尾流涡街的产生,从而实现消除涡流和减少涡生震动的目的.理论分析和实验研究表明,当圆柱表面包覆的电磁场作用参数N＞1,包覆磁场强度B≥0.5 T,流体边界层表面电流密度j为103 A/m2数量级时,对于一般情况下的流场参数而言,流体边界层上的电磁体积力具有十分良好的消涡与减震控制作用效果.优化圆柱体表面的电磁场包覆范围,可以提高电磁消涡减震控制效率.当流体边界层上的电磁体积力方向与流体边界层的流动方向相反时,电磁力又具有显著的增涡增震控制作用效果.