大气的激光监测

在人口稠密的工业区,大气污染已成为严重的问题,研究污染物以及它们和大气组分的反应已成为迫切的需要了.为了预示与日俱增的污染源对环境的影响和采取及时而有效的措施,需要建立大气的数学模型.这些模型的发展、完善和与之相关的连续监测,要求具有广泛的监测功能. 地球上的生命不仅直接或间接地受近地面的大气组分的影响,而且还受到平流层及平流层以上的大气组分的影响.要用合理的成本来恰当地监测这广阔的区域,为此激光监测是唯一可能提供这种功能的技术. 一、大气遥感技术的特点 激光器的发现促进了人们对物质的非线性特性的研究,以及关…     

物理学和天文学

历史上，物理学和天文学的发展是密切联系的。它们在整个现代科学的发展和技术的发达上起到了先锋的作用。物理学的基本规律和天文学提供的广亵的实验室构成了理想的科学发展的基础。20世纪的一系列科学上的重要突破正是这种优良结合的产物。今天，天文学和物理学又共同面对着更新的前测问题，并一道酝酿着新的科学上的重大进展。它们所取得的每一个进展也必然伴随着技术的创新和提高，也不断更新着人类的认识和文明。     

时间,计时标准和原子时钟

一、时间和它的标准问题在这星球土发展、生存和繁衍的人类,他们起始有时间观念恐怕不比有空间的观念来得迟。这种时间观念存在的表现有时是非常自然的。人是生存在三维空间里的,但是人类思维的发展是动的,辩证地开展的,是四维空间的。人类对于时间的感觉,是从因时而异的物质变化而觉察得的。最简单的物质的变化是一种物体的运动。不要以为颐和园门前的铜狮是     

赝标Goldstone玻色子的手征拉氏量的 Gasser-Leutwyler系数

基于我们提出的参数化的完全穿衣服的夸克传播子,我们预言了未知的赝标Goldstone玻色子的手征拉氏量的Gasser-Leutwyler系数Li。预言的G-L系的数值与在文献中广泛应用的经验值和其他许多具有QCD特征的理论模型所预言的值一致。说明参数化的夸克传播子的适用性和可靠性。     

浅谈恒星的演化

在天空里有许多不同种类的恒星,在晴朗的夜晚,你能看到的恒星大多数同太阳十分相似．它们是相当年青的恒星,由于发生在它们中心的所谓热核反应而发光．但还有其他种类的恒星,例如,你在夜空中所看到的几乎呈红色的恒星都是红巨星,还有恒星的遗骸：白矮星、中子星和黑洞,这些小而致密的天体是从其热核燃料资源枯竭的年老恒星产生的． 任何事物的发生、发展总有一定的条件,恒星也是这样,决定恒星演化的因素主要有两个方面,力的问题;能量的问题． 一、恒星的诞生 当气体状的云在其本身的引力作用下开始收缩的时候,恒星的形成过程就…     

磁控溅射气体团簇源中团簇形成的DSMC研究

利用直接模拟蒙特卡洛方法(DSMC) ,模拟了磁控溅射气体团簇源中Cu+ (Cu-)的含量比例不同的条件下,Cu团簇的尺寸分布。模拟结果表明：随着含量比例的增加,团簇的尺寸分布变窄了,不带电的团簇的比例增加,不带电的铜团簇分布的最大值减小,相应的带正电荷和带负电荷团簇的比例减小;相同的含量比例下,带正电的团簇的尺寸分布与带负电荷的团簇的尺寸分布基本相同;初始Cu- 比Cu+ 的含量比例大时,输出的主要是带负电荷的团簇,带正电荷和不带电的团簇占很小的比例;Cu-含量比例的增加,负Cu团簇的尺寸分布减小。     

磁控溅射气体团簇源中团簇形成的DSMC研究

利用直接模拟蒙特卡洛方法(DSMC) ,模拟了磁控溅射气体团簇源中Cu+ (Cu-)的含量比例不同的条件下,Cu团簇的尺寸分布。模拟结果表明：随着含量比例的增加,团簇的尺寸分布变窄了,不带电的团簇的比例增加,不带电的铜团簇分布的最大值减小,相应的带正电荷和带负电荷团簇的比例减小;相同的含量比例下,带正电的团簇的尺寸分布与带负电荷的团簇的尺寸分布基本相同;初始Cu- 比Cu+ 的含量比例大时,输出的主要是带负电荷的团簇,带正电荷和不带电的团簇占很小的比例;Cu-含量比例的增加,负Cu团簇的尺寸分布减小。     

惠斯通电桥实验的分析

惠斯通电桥的灵敏度是影响电阻测量精度的一个主要因素。本论文探究了惠斯通电桥的灵敏度与电源的电动势、桥臂的电阻、桥臂的比例之间的关系。理论分析显示了，电路的总电流保持恒定的情况下，桥臂的比例越大，惠斯通电桥的灵敏度越低，电阻测量的精度越低。另外，桥臂的比例保持不变且电路总电流不大的情况下，电路的总电流越大，惠斯通电桥的灵敏度越高，电阻测量的精度越高。实验测量得到的数据肯定了理论分析得到的结论。     

GW170817:爱因斯坦对了吗?

来自双中子星并合的引力波事件GW170817和伴随的电磁波段的观测,是天文学研究上的一个重要突破。它不仅带给人类史无前例的关于中子星、伽马暴、千新星的知识,也提供了一个检验强场引力的极端天体实验室。爱因斯坦的广义相对论在不同的方面得到了全新的检验,包括引力的速度、引力子的质量、时空的对称性、引力波的辐射和偏振等。这些检验在更高的精度与更广的视角上肯定了广义相对论的预言。     

电势的多级展开与对称性的关系

研究电荷分布在小区域内的情况时,常用多级展开的方法.本文研究了对称分布的带电体的电势场与电多极矩的关系,并用图像的方法说明了电势的各级展开多电荷势的物理意义和叠加形式.从电多极矩的公式出发,分析了有对称性的带电体的电势场与电多极矩的关系,并给出了对称变换的正交矩阵.可以通过电荷分布的对称性,迅速判断多级展开的各级近似是否为零,并进而得到简化的多级展开式.这对加深电多极矩展开内容部分的学习理解和具体计算十分有益.     

脉冲激励下超音速混合层涡结构的演化机理

采用大涡模拟方法对脉冲激励作用下的超音速混合层流场进行数值模拟,所得结果清晰展示了流场中涡结构的独特生长机理.基于涡核位置提取方法,对超音速混合层流场中涡结构的空间尺寸和瞬时对流速度等动态特性进行了定量计算.通过分析流场中涡结构的动态特性在不同频率脉冲激励下的变化,揭示出受脉冲激励超音速混合层流场中涡结构的演化机理:涡结构的生长不再是依靠相邻涡-涡结构之间的配对与融合,而是通过涡核外围的一串小涡旋结构被依次吸进涡核来实现,且受激励流场中各个涡结构的空间尺寸变化较小;流场中的涡结构数量与脉冲频率成正比例关系,而涡结构的空间尺寸与脉冲频率成反比例关系;涡结构的平均对流速度随脉冲频率的增大而减小.针对受脉冲激励超音速混合层,给出了能够表征涡结构特性与脉冲激励参数之间关系的方程式,即受激励流场中涡结构的平均对流速度与脉冲周期的乘积近似等于流场中涡结构的空间尺寸(涡结构平均直径).     

Two-step dissociation of a polaron in conjugated polymers

We have studied the electric-field-driven motion of a polaron by solving the time-dependent Schr\"{o}dinger equation nonadiabatically and the lattice equation of motion simultaneously. It is found that the polaron may experience two sequent transitions under high fields; one is the transition from the subsonic to the supersonic state, and the other from the supersonic to dissociated state. The acoustic mode is decoupled from the charge when the polaron moves at a speed faster than the sound speed, and then the optical mode is decoupled at the second transition to make the polaron dissociate completely.     

Properties and applications of cold supersonic gas jet

By analyzing the formation mechanism of a supersonic gas jet, a set of equations which describe the atomic beam properties were established. The influence of initial temperature, initial pressure, background gas pressure and pumping speed was discussed in detail. A simulation program was developed based on the equations, and the results under different initial conditions were obtained. The results are in good agreement with the experimental data, and suggest that, in order to get much smaller transverse momentum in collision experiments, it is necessary to lower the initial temperature and the initial pressure of the supersonic gas jet, together with increasing the pumping speed. These results are very instructive for construction of a new generation of cold supersonic gas jets.     

导弹超声速尾退分离干扰特性试验

超/高超声速尾退分离在防热、保形、隐身、多次投放、回收等方面具有明显优势,有望成为高超声速飞行器载荷投放的优选方案。由此面临一类新的多体分离问题:超/高超声速尾退分离问题（aft super/hypersonic ejection separation,ASES）。超/高超声速尾退分离问题本质上是带空腔底部流动与多体分离构成的耦合问题,具有流场结构复杂、气动非定常非线性非对称效应显著的特点。针对超声速尾退分离问题,采用网格测力和轨迹捕获（captive trajectory system,CTS）风洞试验方法探索了尾退分离干扰流场的结构,发现可根据流场结构和舵效变化分为低速-亚声速无激波、高亚声速-跨声速弱激波、超声速激波和准自由流弱干扰4种典型干扰特征,揭示了尾流场影响后不同区域的全弹气动特性和舵效特性以及控制律、攻角、高度和Mach数对分离位移和姿态的影响规律。相关结论将有助于增强对尾退分离问题的认识,对尾退分离技术的工程实践具有参考价值。      

Cherenkov-Vavilov formulation of X waves

The field from a supersonic (or equivalently superluminal) point source in uniform motion [i.e., the Cherenkov-Vavilov (CV) effect] is shown to be equivalent to the diffractionless X-wave field. It is demonstrated that the power required to support an X wave is equivalent to the power dissipated by a CV source. In the context of the CV solution, it is clear that any supersonic or superluminal properties exhibited by X waves are purely phase effects. As a consequence, X waves cannot propagate a signal faster than the speed of waves, and thus necessarily obey the law on the finiteness of information transfer.     

Effects of processing parameters on laser cutting of aluminium-copper alloys using off-axial supersonic nozzles

Conventional laser cutting involves the utilization of converging coaxial nozzles to inject the assist gas used to remove the molten material. This processing system prevents the utilization of this technique to cut aluminium alloys for aerospace applications. The inefficient removal of molten material by the assist gas produces cuts with poor quality; very rough cuts, with a large amount of dross, and a large heat affected zone (HAZ) are obtained. An alternative to increase the assist gas performance is the utilization of off-axial supersonic nozzles. Removal of molten material is substantially increased and cuts with high quality are obtained. On the other hand, pulsed laser cutting offers superior results during the processing of high reflectivity materials as aluminium alloys. However, there are no experimental studies which explore the pulsed laser cutting of aluminium alloys by means of a cutting head assisted by an off-axis supersonic nozzle.The present work constitutes a quantitative experimental study to determine the influence of processing parameters on the cutting speed and quality criteria during processing by means of off-axial supersonic nozzles. Cutting experiments were performed in pulsed mode and the results explained under the basis of the molten material removal mechanisms. Performed experiments indicate a reduction in cutting speed as compared to continuous wave (CW) mode processing and the existence of two processing regimes as a function of the pulse frequency. Best results are obtained under the high pulse frequency one (f > 100 Hz) because the superior capabilities of molten material removal of the supersonic jets are completely exploited in this processing regime.     

Active suppression of panel flutter with piezoelectric actuators using eigenvector orientation method

This paper examines the use of eigenvector orientation method to detect the onset of subsonic and supersonic flutter of panels modeled by finite elements. The accuracy of the eigenvector orientation method for prediction of the flutter boundary (indicated by a gradual loss of orthogonality between two eigenvectors) is demonstrated by using the examples of a swept-back cantilever plate model at subsonic speed and a simply supported plate model at supersonic speed. Piezoelectric layers are assumed to be bonded to the top and bottom surfaces of the simply supported plate in order to provide bending moments to control motions of each finite element. An approach of optimal control design is presented to actively suppress the possible flutter based on linear quadratic regulator theory and the nonlinear modal equations of motions. To illustrate the applicability and effectiveness of using the piezoelectric layers as controllers, several cases are studied and presented. The effects of varying locations of control moments are studied so as to fulfill the objective of adjusting the flutter speed to be within a desirable range. The results illustrate that the control moment manipulation can offset the flutter occurrence and additionally generate a lead time for possibly executing flutter control.     

声速测定中“驻波共振”条件的讨论

对超声声速测定仪发射器与接收器之间合成波进行了分析，由此对驻波共振条件进行解释。     

光学窗口凹腔流场的光学传输效应研究

当带有光学成像探测制导系统的高速飞行器在大气层内飞行时,光学窗口与来流之间会形成复杂的凹腔绕流流场,产生气动光学效应。建立了求解超声速流场的高精度LES/RANS混合算法模型,研究了超声速流动条件下的Settles三维凹腔流动;在计算得到精确流场数据的基础上,研究了凹腔剪切层区域的光学传输效应。结果表明,凹腔流动的剪切层结构将引起光线抖动,导致严重的波面畸变,明显降低光强斯特雷尔(Strehl)比,严重影响光学传输性能,进而大大降低光学制导精度。     

Chordwise spacing aerodynamic detuning for unstalled supersonic flutter stability enhancement

Unstalled supersonic flutter is a significant problem in the development of advanced gas turbines because it restricts the high speed operating range of the engine. A new approach to passive control of unstalled supersonic flutter is aerodynamic detuning, defined as designed passage-to-passage differences in the unsteady aerodynamics of a blade row. In this paper, a mathematical model is developed to predict the unstalled torsion mode stability of an aerodynamically detuned turbomachine rotor operating in a supersonic inlet flow field with a subsonic axial component, with the aerodynamic detuning accomplished by alternate chordwise spacing of adjacent rotor blades. The unsteady aerodynamic moments acting on the blading are calculated in terms of influence coefficients. The stability enhancement associated with this alternate chordwise aerodynamic detuning is demonstrated utilizing an unstable twelve bladed rotor based on Verdon's Cascade B flow geometry. This model and unstable baseline rotor configuration are then used to show that axial spacing detuning leads to greater flutter stability enhancement than does circumferential spacing aerodynamic detuning. Finally, the trade-offs between structural damping, alternate chordwise aerodynamic detuning, and alternate circumferential aerodynamic detuning are considered.