尾流的全息成像方法研究

鉴于全息三维成像的独特优点,提出了一种新的尾流测量方法---全息成像测量.在对影响水下全息成像各种因素进行详细理论分析的基础上,自行设计了激光在尾流场的衰减实验和尾流全息成像试验.衰减实验表明,在气泡幕数密度一定的情况下,激光衰减率基本保持恒定;尾流全息成像利用双脉冲激光配合使用4F放大系统首次记录下了气泡幕的全息图像.实验表明,气泡幕全息成像效果良好,证明尾流参量的全息测量方法是可行的.     

尾流的全息成像方法研究

鉴于全息三维成像的独特优点,提出了一种新的尾流测量方法---全息成像测量.在对影响水下全息成像各种因素进行详细理论分析的基础上,自行设计了激光在尾流场的衰减实验和尾流全息成像试验.衰减实验表明,在气泡幕数密度一定的情况下,激光衰减率基本保持恒定;尾流全息成像利用双脉冲激光配合使用4F放大系统首次记录下了气泡幕的全息图像.实验表明,气泡幕全息成像效果良好,证明尾流参量的全息测量方法是可行的.     

尾流光学信号的处理方法

主要利用滤波器、离散傅里叶变换、以及统计信号处理方法等对实验室模拟的尾流信号进行分析和处理、计算.从能量的角度来看,光学信号在有无气泡幕情况下的区别是非常明显的;利用滤波器只能作为尾流光学信号的预处理,从实际应用来看,需要做进一步处理;离散傅里叶变换对不同气压下得到的处理结果存在的区别,必然也为判断不同航速、不同尾龄下的尾流提供了一种线索;以Chirp z变换的形式对尾流光学信号进行处理,使得这种分布具有相当直观的图形,结合适当的图形处理方式,将有可能确定探测尾流光学性质的特征信号.     

Wake structure of a deformable Joukowski airfoil

We examine the vortical wake structure shed from a deformable Joukowski airfoil in an unbounded volume of inviscid and incompressible fluid. The deformable airfoil is considered to model a flapping fish. The vortex shedding is accounted for using an unsteady point vortex model commonly referred to as the Brown-Michael model. The airfoil’s deformations and rotations are prescribed in terms of a Jacobi elliptic function which exhibits, depending on a dimensionless parameter m, a range of periodic behaviors from sinusoidal to a more impulsive type flapping. Depending on the parameter m and the Strouhal number, one can identify five distinct wake structures, ranging from arrays of isolated point vortices to vortex dipoles and tripoles shed into the wake with every half-cycle of the airfoil flapping motion. We describe these regimes in the context of other published works which categorize wake topologies, and speculate on the importance of these wake structures in terms of periodic swimming and transient maneuvers of fish.     

Wake potential in a self-gravitating dusty plasma

Using a test particle approach, the dynamical wake potential has been examined in a homogeneous self-gravitating dusty plasma. The periodic oscillatory potential might lead to an alternative approach to the Jeans instability for the formation of dust agglomeration leading to gravitational collapse of the self-gravitating systems.     

基于MATLAB的尾流图像数字化处理

介绍了尾流图像数字化处理工作原理及方法.用MATLAB软件对船舶时速分别为30km/h和40 km/h的两幅尾流图像进行了灰度变换、滤波、Canny边缘化、二值变换、直方图变换等,并对实验结果进行了初步分析,得到了船舶航速影响尾流边缘夹角、边缘弯曲度及直方图峰值变化.研究结果为尾流图像进入信息化系统提供了基础.     

基于MATLAB的尾流图像数字化处理

介绍了尾流图像数字化处理工作原理及方法.用MATLAB软件对船舶时速分别为30 km/h和40 km/h的两幅尾流图像进行了灰度变换、滤波、Canny边缘化、二值变换、直方图变换等,并对实验结果进行了初步分析,得到了船舶航速影响尾流边缘夹角、边缘弯曲度及直方图峰值变化.研究结果为尾流图像进入信息化系统提供了基础.     

采用脉冲激光探测模拟的舰船气泡尾流

分析了基于后向散射的脉冲激光舰船气泡尾流探测方法,设计并研制了基于该探测方法的实验装置,并在大型水池中对模拟的气泡尾流进行了探测,实验结果表明,该实验装置可以较好地探测到模拟的舰船气泡尾流.     

基于特征值方法的旋翼尾迹稳定性分析

给出一个旋翼尾迹线性化稳定性分析的方法.在该方法中,尾迹涡线被离散为直线涡段,尾迹的扰动归结为涡元端点的扰动,考虑了桨尖涡的自诱导和涡线的互诱导以及桨尖涡与桨叶的实际干扰.使用该方法,分别以UH-1H和AH-1G模型旋翼为例,对悬停和前飞状态的旋翼尾迹的稳定性进行计算和分析.结果表明:旋翼尾迹运动存在大于0的特征值,是内在不稳定的,且最大发散率随波数变化呈现出一定规律性;前飞与悬停状态不同,其最大发散率减小,不稳定性减弱.     

Dynamics of a Swirling Turbulent Wake past a Sphere

Using a mathematical model, which includes the averaged motion equations, differential transport equations of normal Reynolds stresses and dissipation rate, we carried out numerical modeling of evolution of a swirling turbulent wake with nonzero total excess momentum and angular momentum. The calculations were done to very large distances from the body. For small distances from the body the calculated profiles of averaged motion velocities and intensities of turbulent fluctuations of the longitudinal velocity component are in good agreement with the known experimental data of the Lavrent’ev Institute of Hydrodynamics, SB RAS. A simplified model of the flow is constructed.     

稀薄等离子体中激发尾波场的共振条件

研究了在稀薄等离子体中强激光激发尾波场的情况 ,发现尾波场的激发与入射激光的脉冲宽度有共振现象。在光强很小情况下 ,共振所需要的入射激光脉冲宽度为λp 2 ,随着光强的增大共振激光脉冲宽度减小。同时发现在稀薄等离子体中激发的尾波势场与等离子体的密度几乎无关 ,而激发的尾波场最大电场强度与等离子体的密度有关。     

Spectroscopic Detection of Sulfur Oxides in the Aircraft Wake

The absorption/emission spectral regions of SO, SO₂, SO₃, S₂O and HSO are analyzed for the range from UV (λ ≥ 0.2 μm) to IR (λ < 30 μm) and are compared with the atmospheric transmission spectrum. It is shown that many vibrational bands of the compounds considered fall into atmospheric transmission windows. For the vibrational bands of SO, SO₂, SO₃, S₂O, and HSO molecules there are some gases which hinder the absorption diagnostics of the indicated compounds. These interfering gases are natural components of atmospheric air as well as specific gases of aircraft engine exhaust. It is found that the least influence of the interference takes place in the 2400–2700 cm⁻¹ IR region. The spectroscopic techniques used for the detection of aircraft engine exhaust compounds are briefly reviewed, with much consideration given to SO₂. The IR absorption spectra of SO₂ and other gases are calculated for the conditions of the aircraft engine nozzle exit. Narrow spectral intervals suitable for SO₂ detection in a hot flow are determined. An analysis is made for the detection capabilities of CO₂ lasers (including isotope CO₂ lasers) and CO lasers (both fundamental band and first-overtone ones) as applied to SO₂ detection in aircraft engine exhaust. Published in English as Preprint No. 5 of the P. N. Lebedev Physical Institute, Moscow (2004).     

基于激光雷达回波的飞机尾涡参量提取

为了实现对飞机尾涡的有效监测,解决机场飞行安全与跑道容量受限的问题,提出了一种基于激光雷达回波的飞机尾涡参量提取算法.从尾涡的物理模型出发研究飞机尾涡的涡旋环量、径向速度分布等参量,对尾涡结构进行描述.依据尾涡参量的性质,给出了参量提取算法的设计流程,即对回波信号进行分解除噪等处理;通过选取门限确定正负速度包络,进而得到径向速度分布;利用径向速度分布反演得到涡核半径、涡核位置及涡旋环量等尾涡参量.最后以某型飞机的激光雷达探测实验数据为例进行了实例计算并与模型仿真结果进行对比,验证了该算法的有效性.