Universal form of the power spectrum of the aero-optical aberration caused by the supersonic turbulent boundary layer

Based on the measurement of one-dimensional （1D） optical path difference （OPD） of the supersonic turbulent bound- ary layer, an analytical form for the power spectrum of the two-dimensional （2D） OPD is obtained with its structure function and under the locally homogeneous isotropic assumption. The universality of this spectrum is argued, and its validity is checked by the comparison with experimental result. The potential applications of this model in theoretical and numerical studies are emphasized. Another contribution of this work is around the application of correlation function to analyzing the statistics of OPD. Based on our results and other results published elsewhere, we show that the OPD is often not stationary, and one should be cautious about using this tool.

An experimental study of aero-optical aberration and dithering of supersonic mixing layer via BOS

The optical performance of supersonic mixing layer is heavily deteriorated by the aero-optical aberration and dithering of coherent structures, but current measuring methods limit the spatiotemporal resolution in relevant studies. A high resolution whole-field aero-optical aberration and dithering measuring method based on the Background Orient Schlieren (BOS) technique was studied. The systematic structure, sensitivity and resolution of BOS are analyzed in this paper. The aero-optical aberration and dithering of streamwise structures in supersonic mixing layers were quantificationally studied with BOS. The aberration field of spanwise structures revealed the ribbon-like aberration structures, which heavily restrict the optical performance of a mixing layer. The quantifications of aero-optical aberration and dithering are very important in studying aero-optical performance of supersonic mixing layer.

Aero-optical effects simulation technique for starlight transmission in boundary layer under high-speed conditions

Aero-optical effects for starlight transmission in the high-speed flow field will reduce the accuracy of the star sensor on an aircraft.Numerical simulations for aero-optical effects usually require plenty of calculations,which cause difficulties when designing a celestial navigation system for a high-speed aircraft.In this study,an Aero-Optical Simulator For Starlight Transmission(AOSST)in the boundary layer is developed.It effectively reduces the computational burden compared to that of the widely used CFD simulation,and it achieves satisfactory accuracy.In this simulator,gas ellipsoids satisfying certain design rules are used to simulate coherent density structures in boundary layers.Design rules for the gas ellipsoids are found from published experimental and high-fidelity CFD simulation results.The generated wavefront distortion by AOSST is anchored with the scale law for aero-optical distortion in the boundary layer by determining some control parameters,which enables the simulator to output reliable results over a wide range of flight states.Four numerical examples are provided to verify the performance of AOSST.The results demonstrate that AOSST is able to simulate the directional dependence of aero-optical distortions in boundary layers,the variation trend of distorted wavefront shapes with Reynolds number,and the grayscale distribution on the disturbed star map.

A correction method for aero-optics thermal radiation effects based on gradient distribution and dark channel

In this paper, a new algorithm is proposed to remove the effects of aerodynamic optical thermal radiation from a single infrared image. In this method, the joint probability model of gradient distribution is introduced by studying the "global smoothing and local fluctuation" characteristics of the bias field. A prior L0 norm of dark channel is introduced to constrain the latent clear image. Finally, the split Bregman method is used to solve the optimization problem. The effectiveness of the proposed method is verified by a series of experiments, and the results are compared with the results of the existing methods for the correction of thermal radiation effects.

Aero-Optical Characteristics of Supersonic Flow over Blunt Wedge with Cavity Window

The optical rays that form the image of an object and propagate a supersonic flow over a vehicle are refracted by the density variations.A numerical analysis of the aero-optical characteristics of supersonic flow over blunt wedge with a cavity window is carried out.A hybrid method of Reynold averaged Navier-Stokes and direct simulation Monte Carlo(RANS/DSMC) is employed to simulate the flowfield.Refraction factor is introduced to evaluate the flowfield's aero-optical characteristic.The results show that mean flow's aero-optical effects are mainly caused by the shock wave,the expansion wave and the turbulent boundary layer.Fluctuation flow's aero-optical effects are mainly caused by the turbulent boundary layer and the shock wave induced by the cavity window.The aero-optical effects at the leading side of window are caused by the mean density variations,while the effects at the trailing side are caused by the density fluctuations.Different draft angles of the cavity window are investigated.The airborne optical devices of supersonic vehicle should be mounted in the middle of the cavity window with a large draft angle.

Inhibition of the aero-optical effects of supersonic mixing layers based on the RVGAs'control

The infrared imaging windows of the hyper/supersonic optical dome are encountering severe aero-optical effects[AOEs],so a flow control device,the ramp vortex generator array[RVGA]is proposed based on the ramp vortex generator to inhibit the supersonic mixing layers’AOE,which is done by the nanotracer-based planar laser scattering technique and ray-tracing method.The experiments prove that under different pressure conditions,RVGA can reduce the mean and standard deviation of the root mean square of the optical path difference[OPDrms]and reduce the supersonic mixing layers’thickness and mixture a great deal.The AOE of the pressure-matched mixing layer is the weakest.Higher RVGA results in better optical performance.RVGA has the potential to be applied to supersonic film cooling to reduce aero-optical aberrations.

Aero-optical aberration measuring method based on NPLS and its application

The existing methods for measuring aero-optical aberration suffer from several problems,such as low spatiotemporal resolution,sensitivity to environment,and integral effects.A new method for measuring aero-optical aberration of supersonic flow is proposed.Based on the self-developed measuring method of supersonic density field,the wavefront aberration induced by a cross-section of supersonic flow field could be measured by ray-tracing.Compared with other methods,the present one has three significant innovations:(1) high spatiotemporal resolution.Its time resolution is 6 ns,and the spatial resolution can reach up to micrometers;(2) it can avoid the integral effects and study the wavefront aberration induced by the flow field of interest locally;(3) it can also avoid the influence from the test section wall boundary layers and environmental disturbances.The present method was applied to supersonic flow around an optical bow cap.The results of high spatiotemporal resolution reveal fine wavefront structures,and show that shock waves,expansion waves and turbulent boundary layers have different impacts on the wavefront aberration.

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.

高速飞行器气动光学效应

采用数值模拟、计算光学方法和理论,对超声速飞行器流场进行数值模拟研究,获取不同飞行高度和攻角下光学窗口上方流场的密度分布,根据Gladstone-Dale关系得到光学窗口上方的折射率场,利用光线追迹法计算流场光程差分布情况。对流场光程差的分布情况进行分析,可以得出结论:随着飞行高度的增加,气动光学效应逐渐减弱;随着攻角的增大,气动光学效应逐渐增强。

航空发动机叶片装配执行过程智能检测及AR引导

为了提高航空发动机叶片装配执行过程的作业智能化程度,本文提出一种航空发动机叶片装配执行过程智能检测及AR引导方法,该方法包括叶片编码识别、物料AR出入库和齐套摆放过程状态检测3个环节。针对航空发动机叶片物料缺乏自动化识别和智能化纠错的问题,搭建基于编码识别的叶片物料管理架构,提出基于图像处理的叶片编码图像前处理增强操作,并利用贝叶斯纠错对识别结果进行正误判断和纠错校正的后处理操作,提高了叶片编码识别准确率;在物料人工出入库环节,利用AR增强可视化信息辅助用户快速执行作业任务,降低了叶片物料选取作业的时间;针对叶片物料齐套准备过程,构建了基于检测比对的防错纠错系统,避免发生人为错误。所提叶片装配执行过程智能检测及AR增强辅助引导方法可以有效减少人力物力和时间消耗,在推动航空发动机迈向智能化和自动化生产上起到技术支撑作用。

类THAAD导引头气动光学效应计算研究

针对类美国末段高空域防御(Terminal High Altitude Area Defense,THAAD)系统的红外导引头外形,开展了气动光学效应计算分析,并将其用于飞行器设计。利用国家数值风洞工程高速流场计算软件NNW-HyFLOW,考虑热化学非平衡效应和材料传热耦合效应,对导引头典型状态的流场进行了模拟,获得了流场的密度、温度、压力等参数和窗口的温度场参数。基于流场参数,利用HyFLOW气动光学传输效应计算功能,开展了红外光学传输成像计算;利用HyFLOW气动光学辐射效应计算模块,开展了流场和光学窗口的热辐射计算。计算结果表明,类THAAD导引头在30 km以上飞行时,流场和光学窗口基本不会影响目标信号的光学传输成像,但流场和窗口的热辐射效应会对导引头识别目标造成影响。不过随着飞行高度的升高,这种影响会减小。

机载激光通信光学窗口气动光学效应分析

机载激光通信中通信光束散角小、系统跟踪精度高,光学窗口的气动光学效应会引起远场光斑形状和位置发生变化,降低通信性能。为此,通过Fluent对共形和平面两种光学窗口整流罩在不同飞行高度、速度、方位角下的外流场进行稳态仿真分析,利用相位屏分析远场自由衍射光斑变化。结果表明,共形窗口在俯仰、高度和速度变化中的流场更加稳定,呈现更为一致的变化趋势,且在远场衍射中表现更好。平面窗口在方位转角变化大与低速的飞行工况下,RMS值低于共形窗口。远场光斑发生偏移和弥散的程度与波面畸变成正相关,但在波面畸变较大的情况下,RMS值不能完全定义其对光学系统的影响。同时,当俯仰角靠近机体表面、降低飞行高度、增加飞行速度均会增强波面畸变。

紫外像增强器在航空发动机燃烧诊断中的应用

航空发动机燃烧过程中,OH^(*)、NO^(*)、NH^(*)等激发态自由基伴随着紫外波段的微弱自发光,且随燃烧的进程而快速变化。紫外像增强器最高具有百万倍电子增益、纳秒量级快门,可以实现紫外波段燃烧流场瞬态结构的捕获,为定量化测量、阐释燃烧特性随多物理参数的变化规律奠定基础。本文总结紫外像增强器在航空发动机燃烧光学诊断中的应用,包括针对OH^(*)自发光进行成像的被动光学诊断技术、利用激光激发OH成像的主动光学诊断技术等。最后,结合新型航空发动机高时空分辨探测的要求,指出紫外像增强器在燃烧诊断中的发展方向。

基于光纤传感的航发齿轮动应力测试与振动特性研究

基于光纤传感技术,研究高速圆柱齿轮辐板动应力测试方法,并针对某型发动机附件传动圆柱齿轮齿根裂纹故障问题,测量得到该齿轮在实际工况下的动应力数据。结果表明:随着转速的增加,齿轮副表现出异常振动状态;实验所得数据的频谱分析显示,主要分频在8100 Hz附近幅值具有明显变化;啮合频率(8047 Hz)与第3节径固有频率(8313.9 Hz)接近,推断故障齿轮在转速14200 r·min^(-1)下存在3节径共振。

风洞试验中的视频测量技术现状与应用综述

视频测量(Videogrammetric Measurement,VM)技术因其对试验模型的设计制造无要求,受到国内外风洞试验机构的青睐,本文综述了国外航空航天强国的风洞试验机构所掌握的VM技术,并分析了VM技术在我国高速暂冲风洞试验中应用所面临的问题,据此中国空气动力研究与发展中心(CARDC)提出了多相机动态标定与基于运动估计的序列图像匹配技术,在暂冲高速风洞高噪声(130dB左右)振动环境下,建立了高精度的模型位姿光学测量技术,2米量级高速风洞中的多个应用表明:视频测量的精度高,已用于高速试验模型的姿态与变形测量;另一方面,通过VM测量偏折位移场得到光束从摄影中心出发穿过扰流区的光程差,为气动光学效应的研究与测量以及试验模型的壁面流动显示提供新的途径,其光路简单、无需使用价格昂贵的相干光源,因此具有巨大应用前景。

红外目标图像循环迭代复原算法的加速技术研究

为了提高图像处理的实时性,本文针对作者先前提出的循环迭代图像复原算法迭代次数多、收敛速度慢等问题,提出了一种基于线性搜索的加速迭代技术.该加速技术利用泰勒级数展开式根据当前次的迭代结果对下次迭代数据进行预测,合理地跳过原有的一些迭代点,从而加快算法收敛.在达到相同复原效果条件下,减少了迭代次数,提高了算法的实时性.本文对收敛加速技术进行了理论分析和推导,在微机上进行了一系列的对比实验,实验结果表明,本文给出的加速技术效果显著,获取了加速因子的有效取值等一些有用的实验参数,算法具有实用价值.

超高声速飞行器光学窗口气动光学效应分析

超高声速飞行器在大气中飞行时,由于气动热和气动力的作用,光学窗口会产生严重的气动光学效应,使目标图像发生像偏移、抖动、模糊和能量衰减。利用有限元分析方法对光学窗口的热光效应、弹光效应和窗口热变形进行研究,计算了由热光学效应、光学窗口热变形引起的点扩散函数峰值大小及峰值位置(像偏移)随时间的变化趋势。根据对温度场的分布分析,计算了温度梯度对透过率的影响以及透过率与窗口热辐射随时间变化的趋势,可为光学窗口的设计、材料的选择及后期的图像处理提供依据。

机载激光通信中气动光学的影响及补偿

为了抑制机载激光通信中大气附面层引起的散斑现象,开展了气动光学效应及相应补偿方法的研究。从理论上分析了气动光学效应对光传输的影响;根据试验飞机型号和设备安装位置,对光学窗口形状、厚度等参数进行了优化设计,并对窗口变形和空气流场分布进行了仿真分析,完成了光学窗口改造。最后,根据试验中大气附面层引起的接收光斑离焦现象,进行了光学仿真,研制了3种焦距的补偿镜。在飞行距离为10~140km,飞行高度为1 500~4 500m条件下进行了飞行试验,对不同补偿镜的补偿效果进行了分析。结果显示,在接收光路中增加焦距为5.5×105 m的凸透镜后,接收光斑离焦现象得到了抑制,接收光功率闪烁方差减小了1/3,表明经过补偿后的光学窗口可有效抑制大气附面层对激光通信的的影响。

高速风洞试验中的视频测量技术进展

视频测量(Videogrammetry)技术因其对试验模型设计无特殊要求,受到国内外风洞试验机构的青睐。本文在介绍视频测量的理论基础之上,面向高速风洞试验的振动噪声环境,分析了飞行器精细化风洞试验对视频测量技术的需求,综述了大角度大重叠数字图像的外方位元素解算、标记点及其图像处理、相机标定和气动光学波前畸变场测量等技术进展。在2m量级的高速风洞中,通过多个工程实例表明:视频测量的精度高,同期试验迎角视频实测数据的标准差≤0.0075°;同期动态变形实测数据的标准不确定度为5.232±0.082mm;为气动光学效应的研究与测量提供了新途径,其光路简单、无需使用价格昂贵的相干光源。

高马赫飞行器迎风面与攻角对光学窗口周围流场的影响分析

为了提高高马赫飞行下光学窗口的光学性能,对比分析了基于气动光学效应三种飞行器模型不同攻角的马赫数场、密度场、温度场和压力场的流场结构及对光学性能的影响。首先,根据飞行器与来流的迎风面,建立了三种飞行器典型模型;继而,给出了0°、5°和10°攻角飞行工况;然后,建立了基于Navier-Stokes方程和湍流模型的三种攻角流场分布;最后,对比分析了宽平头体飞行器中三种攻角温度场作用下的光学系统传递函数。结果表明,马赫数场与密度场、温度场与压力场分别具有相似分布形式;相同飞行速度和攻角下,大迎风面的飞行器光学窗口周围温度与压力较小迎风面大;相同飞行器,较大攻角对应较大流场强度,攻角为0°、5°和10°时传递函数分别为0.188,0.097和0.028。此分析结果可为高马赫飞行下光学窗口优化提供一定的理论依据。