Algorithm for determining the aerodynamic characteristics of a freely flying object from discrete data of ballistic experiment. Part 2

In part 1 of this paper, an algorithm for numerically solving the inverse problem of motion of a solid through the atmosphere is described that constitutes the basis for identifying the aerodynamic characteristics of an object from trajectory data and the respective identification procedure is presented. In part 2, methods evaluating the significance of desired parameters and adequacy of a mathematical model of motion, approaches to metrological certification of experimental equipment, and results of testing the algorithm are discussed.     

Algorithm for determining the aerodynamic characteristics of a freely flying object from discrete data of ballistic experiment. Part I

In part 1 of this paper, an algorithm for numerically solving the inverse problem of motion of a solid through the atmosphere is described that constitutes the basis for identifying the aerodynamic characteristics of an object from trajectory data and the respective identification procedure is presented. In part 2, methods evaluating the significance of desired parameters and adequacy of a mathematical model of motion, approaches to metrological certification of experimental equipment, and results of testing the algorithm are discussed.     

Model of a neural network inertial satellite navigation system capable of estimating the earth’s gravitational field gradient

A model for recognizing inertial and satellite data on an object’s motion that are delivered by a set of distributed onboard sensors (newtonmeters, gyros, satellite receivers) has been described. Specifically, the model is capable of estimating the parameters of the gravitational field.     

基于不动点理论的多系统兼容接收机频点选择问题的研究与遗传算法实现

基于不动点理论研究了多系统兼容接收机的频点选择问题,并引入遗传算法解决了这一问题.将Banach不动点理论引入频点空间,提出并证明了频点空间中频点集的遗传进化过程反映了频点空间呈现出的一种不动点物理特性;经过频点空间算子的足够多次的反复遗传进化作用,频点空间中的任一迭代序列源频点集都将最终收敛于唯一不动点目标频点集,而该不动点目标频点集中的目标频点即为该频点选择问题的最优解.完成了遗传算法应用于频点选择问题的理论研究与实现.仿真结果表明,该算法能够有效地解决多系统兼容接收机的频点选择问题. 关键词： 多系统 接收机 遗传算法 不动点     

基于光流的运动小目标检测算法

运动目标的检测是目标识别与跟踪的关键技术之一。光流技术是一种以物体的运动特征来检测目标的方法,它的提出为运动小目标的检测开辟了新的空间。在一个搜索跟踪系统中使用光流技术检测和跟踪空中小目标,目标大概为5～10个像素,而且背景复杂,相机抖动,普通分割算法无法得到小目标。在目标的运动明显异于背景的情况下,通过利用基于光流的目标检测算法来检测出小目标,同时运用高斯金字塔模型,提高算法的运算速度。试验结果表明提出的基于光流的检测算法在背景运动的红外图像中取得了较好的效果。     

A numerical study of the effects of design parameters on the acoustics noise of a high efficiency propeller

A numerical study of a high efficiency propeller in the aerodynamic noise generation is carried out. Based on RANS, three-dimensional numerical simulation is performed to obtain the aerodynamic performance of the propeller. The result of the aerodynamic analysis is given as input of the acoustic calculation. The sound is calculated using the Farassat 1A, which is derived from Ffowcs Williams–Hawkings equation, and compared with the data of wind tunnel. The propeller is modified for noise reduction by changing its geometrical parameters such as diameter, chord width and pitch angle. The trend of variation between aerodynamic analysis data and acoustic calculation result are compared and discussed for different modification tasks. Meaningful conclusions are drawn on the noise reduction of propeller.     

扩压器入口面积比对自由旋涡气动窗口性能的影响

 针对采用主动式扩压器的自由旋涡气动窗口,实验考察了扩压器入口面积比对扩压器压力恢复性能及自由旋涡气动窗口密封性能的影响。结果表明：入口面积比是影响扩压器压力恢复性能的重要因素;通过优化扩压器入口面积比,可以提高气动窗口密封压比和稳定性。主动式扩压器比传统扩压器具有更小的最佳入口面积比,使气动窗口射流更接近于理想自由旋涡射流;主动式扩压器最佳入口面积比约为2.03。在最佳入口面积比情况下,扩压器内端壁吹气临界驻室压力最低,外端壁吹气压力对密封压力基本没有影响。     

Precise speed measurement using an interlaced scan image

In this paper, we propose a novel scheme for speed measurement of a moving object with translational motion. First, this scheme uses one interlaced scan CCD camera to obtain only one interlaced scan image of a moving object. The odd and even field images are extracted and resized. Second, image matte is applied in these two field images to extract the moving object’s silhouettes. The distance between two centroids in the two silhouettes is then computed. Finally, the object’s speed is calculated using the above distance and the camera imaging parameters. Simulation and real experiments prove that our scheme can fulfill the speed measurement for translational motion accurately.     

直升机旋翼桨叶气动力学参数飞行测试系统

根据某型号直升机定型试飞的需要,研制出了动态测量旋翼桨叶气动力学参数的光电测试系统。其中运动参数(挥舞角、摆振角和变距角)由二维位置敏感传感器响应桨叶表贴发光点的位置变化测得,挥舞应变由光纤光栅传感器测得。利用自主搭建的桨叶运动姿态仿真平台开展了相关测试实验。结果表明:各角度值与对应输出电压间有很好的线性关系,测量范围内的角度测量误差小于1%;光纤光栅与电阻应变片对比测试的一致性较好,线性相关系数达到了0.999;光纤光栅应变测量的复现性很好,两次应变测量的相对偏差仅为1.22%。系统具有较高的测试精度。     

电动水上飞机低噪声螺旋桨翼型优化

为降低翼型的气动噪声,以某型电动水上飞机螺旋桨所使用的RAF-6翼型为研究对象,首先通过CFD/FW-H方法计算得到翼型的升、阻力系数以及气动噪声;其次使用型函数线性叠加描述翼型的几何形状;进而,为使翼型获得设计状态下较好的声学与气动性能,由翼型的气动噪声与升阻比构成优化目标,以型函数系数为变量,以保证翼型升、阻力系数变化不超过10%为约束,使用引入响应面模型的遗传算法对翼型进行降噪优化。通过优化翼型与基准翼型的对比可知,设计状态的优化翼型气动噪声声压级降低了2.17 dB,升阻比提高1.12%,且优化翼型在小攻角状态下具有较为优异的声学与气动性能。优化结果表明,该优化方法具有一定应用价值,可为螺旋桨噪声控制研究提供参考。     

旋转扫描式成像光谱仪高光谱的几何变形矫正

Offner成像光谱仪是一种线推扫式成像系统,需要光谱仪与物体之间存在相对移动,从而记录整个区域的光谱和形貌信息。在光谱仪镜头前放置一块反射镜进行旋转扫描,也可以对大尺度物体进行高光谱成像,并且相机固定不动。然而旋转扫描时,记录的高光谱图存在较大的几何误差。该工作分析一般情况下Offner成像光谱仪单次拍摄得到的物点和像点的投影关系;根据投影关系,以旋转角为变量,分析物点在成像面上的投影分布,给出图像几何变形的矫正方法。在成像光谱仪上设计并安装了反射镜旋转扫描装置,进行旋转扫描实验,通过矫正算法,得到了清晰的高光谱图。     

飞机尾焰红外图像采集与分析

介绍了超音速机载红外测量吊舱系统(以下简称红外测量吊舱)中红外探测器的选型,以及在测量目标机亚音速飞行时飞机尾喷口及飞机尾焰的电视和红外热图,并对跟踪空中飞行目标所采集到的红外尾焰热图作了细致的分析和计算,从而为空中目标的红外特性检测分析、研究提供了有效的数据积累.     

二维轴对称图象高阶胡氏不变矩快速算法的改进

提出了基于二维轴对称性目标图象矩快速算法的实用化改进方案.算法实用化改进是通过两个命题的证明实现的.一是通过轴对称目标图象质心在对称轴上的命题证明,实现了将二维轴对称图象矩快速算法用于轴对称性图象中心矩的计算;二是通过目标图象以坐标系中任意两点为圆心,旋转相同角度,结果图象具有平移性的命题证明,实现了算法用于对旋转不同角度的对称目标图象的中心矩的计算改进.在此基础上,完成了二维轴对称目标图象高阶胡氏不变矩实用化快速算法的实现.实验证明,该算法具有较好的实时性能,且具有较小的引入误差.     

A high-efficiency aerothermoelastic analysis method

In this paper,a high-efficiency aerothermoelastic analysis method based on unified hypersonic lifting surface theory is established.The method adopts a two-way coupling form that couples the structure,aerodynamic force,and aerodynamic thermo and heat conduction.The aerodynamic force is first calculated based on unified hypersonic lifting surface theory,and then the Eckert reference temperature method is used to solve the temperature field,where the transient heat conduction is solved using Fourier’s law,and the modal method is used for the aeroelastic correction.Finally,flutter is analyzed based on the p-k method.The aerothermoelastic behavior of a typical hypersonic low-aspect ratio wing is then analyzed,and the results indicate the following:(1)the combined effects of the aerodynamic load and thermal load both deform the wing,which would increase if the flexibility,size,and flight time of the hypersonic aircraft increase;(2)the effect of heat accumulation should be noted,and therefore,the trajectory parameters should be considered in the design of hypersonic flight vehicles to avoid hazardous conditions,such as flutter.     

基于大数据的高速列车气动载荷作用下迭代学习主动控制研究

列车在高速运行的过程中与另一列车相交会时,将产生剧烈的瞬态气动载荷冲击而引起车体瞬间横向振动加剧,导致列车横向平稳性恶化。为了改善列车运行平稳性,采用大数据方法及迭代学习控制思想,提出基于高速列车运行大数据的迭代学习主动控制算法,并进行多体动力学与控制算法的联合仿真,进一步研究控制算法对会车气动载荷幅值变化和会车时间变化的鲁棒性。结果表明：大数据迭代学习主动控制经过5次迭代后对会车气动载荷激扰下的车体横向振动峰值降低52.67%,且控制算法对会车工况变化有较好的鲁棒性。     

A simplified approach for the generation of projection data for cone beam geometry

To test a developed reconstruction algorithm for cone beam geometry, whether it is transmission or emission tomography, one needs projection data. Generally, mathematical phantoms are generated in three dimensions and the projection for all rotation angles is calculated. For non-symmetric objects, the process is cumbersome and computation intensive. This paper describes a simple methodology for the generation of projection data for cone beam geometry for both transmission and emission tomographies by knowing the object’s attenuation and/or source spatial distribution details as input. The object details such as internal geometrical distribution are nowhere involved in the projection data calculation. This simple approach uses the pixilated object matrix values in terms of the matrix indices and spatial geometrical coordinates. The projection data of some typical phantoms (generated using this approach) are reconstructed using standard FDK algorithm and Novikov’s inversion formula. Correlation between the original and reconstructed images has been calculated to compare the image quality.     

Identification of aerodynamic characteristics with discontinuities of the first kind from trajectory data for a free-flying object

A method is proposed for identifying the aerodynamic characteristics of a model the flow about which varies considerably in the course of motion. In this method, the trajectory of the model is split into sections with different types of the flow and then similar data from these sections are collected into groups and processed. The aerodynamic characteristics are identified by the method of successive approximation using a differential correction algorithm. The accuracy of the results is analyzed.     

基于自适应共振神经网络的单粒子激光电离质谱数据分析

气溶胶激光飞行时间质谱仪(ALUOFMS)可以在线地对气溶胶单粒子进行物理和化学特性分析,利用双束连续激光对单个粒子的空气动力学粒径进行测量,并通过飞行时间完成单粒子化学成分的检测。该仪器在运行过程中将产生海量的实验数据,对这些数据快速、自动处理并提取有价值的信息是整机系统的关键之一。文章介绍了基于神经网络的自适应共振算法(ART-2a)在随机混和的氯化钠、氯化钙、邻苯二甲酸二正辛酯(DOP)和2,5二羟基苯甲酸(DHB)气溶胶单粒子聚类分析中的成功运用。同以往的质谱分析方法相比,ART-2a可以实现对任意多和任意复杂的输入模式进行自组织,自适应和自稳定的快速识别,更有利于质谱数据的分析。实验结果表明,当警戒值为0.40,学习速率为0.05以及迭代次数为6时,ART-2a可以成功地对这四种物质进行分类,同时得到4类物质的聚类中心,每类的聚类中心都能很好的代表该类物质的特征。     

激光烧蚀等离子体射流与固体靶相互作用实验研究

利用激光烧蚀等离子体射流可以获得数km/s 甚至上千km/s 的射流速度，远超目前绝大多数设备所能提供的模拟速度，并且覆盖了极大的温度与密度范围，作为加载手段具有广阔的应用前景。通过实验方法，探索和发展激光烧蚀等离子体射流这一新型实验模拟手段，利用高功率激光烧蚀产生高温高压等离子体射流，实现超高速气体动力学实验室模拟的新途径。以此作为加载条件，研究超高速物体与气体相互作用的气体动力学特性。通过建立激光烧蚀等离子体射流与固体靶相互作用实验方法，可进一步研究等离子体射流的产生、发展以及高速物体气体动力学，为下一步开展天体物理、小行星形貌、超高速陨石与行星大气相互作用机制等相关研究奠定基础。     

天文图像多帧盲反卷积收敛性的增强方法

天文图像多帧盲反卷积的收敛性受到初始目标、约束条件和光子噪声等因素的影响.提出了用实际光学成像系统参数确定频率带宽有限约束的方法.用Knox-Thompson 方法重构初始目标相位形成盲反卷积算法的初始目标函数.研究了一种新颖的有效减小光子噪声、边缘效应和振铃现象的方法.根据最大似然估计理论，用期望最大化的优化方法建立了改进的严格约束多帧盲反卷积算法.模拟图像和实际天文图像的复原结果表明，所建立的多帧盲反卷积，可以有效克服大气湍流和减小光子噪声，改善天文观察图像的分辨率，并部分消除光学系统衍射效应对恢复图像的影响. 关键词： 大气光学 天文观测 图像处理和恢复