蒸发液滴空间实验研究的图像反馈控制系统

提出了一种利用图像反馈控制系统测量液滴蒸发速率的方法.该系统主要由图像采集、图像处理、反馈控制三个部分组成.其工作原理是对CCD采集到的液滴图像进行分析,得到液滴的物性参数,利用控制注液器动态注入来维持液滴的大小,由此得到单位时间内的注入量,即液滴蒸发速率.或通过对液滴图像几何尺寸的计算,得到单位时间内液滴的变化量,进而得到液滴的蒸发速率.为了从动态变化的图像中准确找到液滴的轮廓,简单介绍了基于拉普拉斯方程,运用牛顿法和龙格库塔法等数值方法,对图像轮廓进行拟合的算法理论.以拟合得到的液滴轮廓为基础,利用数值积分计算液滴的表面积和体积,从而由体积的变化量确定蒸发速率.介绍了图像反馈控制系统的软件结构和硬件结构.并给出了利用其进行液滴蒸发测量得到的实验结果.该系统是为我国SJ-10返回式卫星上蒸发与流体界面效应空间实验研究项目专门开发的.      

非均质壁面对液滴俘获能力的数值模拟研究

为研究不同非均质壁面对液滴的俘获能力,采用界面追踪法（FTM）结合广义滑移边界建立了接触角模型,对液滴在非均匀润湿的非均质壁面上的运动过程进行了数值模拟研究。液滴在倾斜壁面上受到重力作用由均匀润湿部分下滑至非均匀润湿部分,通过改变Bo数、Oh数、非均匀润湿程度研究了液滴在非均匀润湿区域的运动规律。研究表明:Bo数越大,液滴运动受壁面阻力影响越小,液滴下滑的速度越快,液滴越难以被俘获;Oh数越大,液滴运动受壁面阻力影响越小,液滴越难以被俘获;非均匀润湿程度越大,非均质壁面对液滴的阻力越大,液滴越易被俘获。      

Thermocapillary migration of bubbles and droplets

The migration of a droplet in a large liquid body possessing a uniform temperature gradient is analyzed in the creeping flow limit for small values of the Marangoni number (ε). The method of matched asymptotic expansions is used for the solution of the field equations. The migration velocity is calculated to 0(ε²) and the result reduces to that of Young, Goldstein and Block [10] in the limit of zero Marangoni number.     

多级降压调节阀内部流动特性数值模拟

为研究多级降压调节阀内部流动过程和各降压级的压降影响因素及规律,基于Mixture两相流模型和Schnerr-Sauer空化模型的数值计算方法,建立了多级降压调节阀内部流场的计算模型。通过数值模拟计算,获得了调节阀内部的流动特性,分析和探讨不同压差和不同阀门开度下各降压级压降特性。数值计算结果表明：流体流经阀门节流元件时,由于多股流体的强烈掺混和剪切使得阀门内存在大量的漩涡;各降压级的压降存在一定的差异,第3级套筒处的空化程度最大,阀座处更易发生空化;阀门在同一开度下,工质沿各降压级的压降在不同压差下的变化趋势相同;第3降压级的压降随阀门开度的减小而增大,在25%开度下阀门第3降压级的平均压降最大,达到了8 MPa,相同流量下该降压级小孔中工质的速度也增加。研究结果为降压阀的合理设计提供了理论依据和参考价值。     

富氢/富氧燃气同轴直流喷嘴燃烧过程数值模拟

为研究全流量补燃FFSC(Full Flow Staged Combustion)循环发动机气-气喷注器性能,以气氢/气氧(GH2/GO2)预燃室提供的758K富氢燃气和676K富氧燃气为推进剂对同轴直流喷嘴燃烧流场进行了数值模拟.考察了相同燃烧室结构、流量、入口燃气温度条件下,富氧燃气压降、富氢燃气和富氧燃气的速度比、氧喷嘴厚度和氧喷嘴缩进变化对燃烧性能的影响,获得了4个参数的影响规律.数值模拟结果对燃气气-气喷注器结构设计有参考价值.     

橡胶颗粒振动流化床中流体力学行为的研究

为了探讨振动流化床中颗粒的流体力学行为,在振动流化床常温实验装置上,以橡胶颗粒为试料,研究了较低开孔率下振动强度、床层高度、气速等参数对振动流化床床层压降的影响.分析了起始流态化速度随床层高度和振动强度改变的变化规律.并把实验结果同文献中尼龙1010的实验结果进行了对比,得到了有益的结论.对橡胶颗粒振动流化床中流体力学行为的研究可为低温粉碎中橡胶颗粒的低温气固传热研究给出合理的建议.     

On the generation of satellite position (and velocity) by a mixed analytical-numerical procedure

The generation of accurate Earth-satellite ephemerides by numerical integration, over a period of perhaps weeks, can consume an inordinate amount of computer time. No satisfactory purely analytical procedure exists, but if short-period components of the standard elliptic elements are removed analytically, the resulting mean elements can be integrated with a step time that is longer than the satellite's orbital period.The definition of the mean elements depends on the particular perturbations included in the orbit generator and regarded as non-resonant. It is best if short-period perturbations are not applied to the orbital elements themselves but to the satellite's position (and velocity if required), expressed in a system of cylindrical polar coordinates, and the paper shows how mean elements can be recovered from position and velocity.A computer program has been written to test the proposed procedure for generating ephemerides, using a truncated potential field. Some results from this program are presented.     

The X-ray properties of accreting black holes

Accreting black holes in binary systems exhibit two properties that distinguish them from the vast majority of binary X-ray sources: (1) rapid ≤ 1 s variability and (2) bi-modal spectral behaviour. These findings are based primarily on the observed properties of Cyg X-1 where an estimate of the X-ray source mass from radial velocity studies indicates a mass of 10 M. The recently suggested black hole candidacy of LMC X-3 is based on a similar mass estimate. The X-ray properties are similar to those of Cyg X-1 in its “high state”. The unique spectral properties of these systems are used to search for other similar systems, and new “possible” candidates are suggested, that include several transient sources. A possible spectral connection between these systems and their more massive counterparts in AGN is discussed.     

微重力环境下半球形贮箱液体重定位试验研究

本文利用落塔形成的微重力环境,对半球形贮箱中液体重定位问题进行了试验研究。所用液体与半球形箱壁之间的接触角为零并在加载前形成了失重初始凹液面.本试验分侧向不加干扰及加干扰两种初始条件.通过高速摄影机观察了液体重定位的全过程并测量了重定位流速和重定位时间。试验结果表明,液体重定位呈壁流流型.实测重定位时间与理论估算值一致.      

High-cadence Hα imaging of solar flares

The Hα observation is a powerful tool to study the high-energy aspect of solar flares. Spiky brightenings of flare kernels at the Hα center reflect the rapid fluctuation in particle acceleration; linear polarization of Hα emission might be evidence of accelerated protons; red-shifts of the Hα line are caused by the chromospheric evaporation. To study the spiky brightenings of flare kernels with high-cadence imaging at the Hα center, a high-speed Hα camera for the Solar Flare Telescope at Mitaka, NAOJ, had been developed and it started the regular observation in 2001 July. However, the polarimetry and the Dopplermetry are also important and they are required to be carried out in parallel with the high-cadence imaging at the Hα center. Then, we upgraded the original high-speed Hα camera to a new Hα camera system for the multi-aspect Hα observations, which performs all of the high-cadence imaging, the linear polarization measurements, and the off-band imaging for velocity measurements. The new system started the observation in 2002 July. In this paper, the multi-aspect Hα imaging system is described and sample Hα images are presented.     

气泡雾化喷嘴水平喷射的雾化特性研究

研究了水平喷射、端面注气方式的气泡雾化喷嘴结构及工作参数对雾化及流场特性的影响.试验全部在常温常压下进行,液体采用水,雾化气为压缩空气.用2D PDA测量了液雾的平均直径尺寸分布和速度分布.液体喷射压力变化范围200~600 kPa,气液比变化范围4%~10%左右.试验研究了端面注气方式下,注气孔孔径及数目、混合管长度、液体流动状态及工作参数对雾化特性的影响.结果表明,水平喷射的气泡喷嘴,注气孔的尺寸及数目均对雾化特性产生影响;混合段存在一最佳值范围,在此范围内,喷嘴可获得高的雾化质量;液体旋转流动对雾化特性无显著影响,但可影响两相流动中气泡的分布.     

Scientific results from the pioneer Saturn infrared radiometer

The Pioneer 11 Infrared Radiometer instrument made observations of Saturn and its rings in broadband channels centered at 20 and 45 μm and obtained whole-disk information on Titan. A planetary average effective temperature of 96.5±2.5 K implies a total emission 2.8 times the absorbed sunlight. Correlation with radio science results implies that the molar fraction of H₂ is 90±3% (assuming the rest is He). Temperatures at the 1 bar level are 137 to 140 K; regions appearing cooler may be overlain by a cloud acting as a 124 K blackbody surface. A minimum temperature averaging 87 K is reached near 0.06 bars. Ring boundaries and optical depths are consistent with those at optical wavelengths. Ring temperatures are 64–86 K on the south (illuminated) side, ～54 K on the north (unilluminated) side, and at least 67 K in Saturn's shadow. There is evidence for a south to north drop in ring temperatures. Titan's 45 μm brightness temperature is 75±5 K.     

Evaluation of gravity-dependent membrane potential shift in Paramecium

It is still debated whether or not gravity can stimulate unicellular organisms. This question may be settled by revealing changes in the membrane potential in a manner depending on the gravitational forces imposed on the cell. We estimated the gravity-dependent membrane potential shift to be about 1 mV G⁻¹ for Paramecium showing gravikinesis at 1–5 G, on the basis of measurements of gravity-induced changes in active propulsion and those of propulsive velocity in solutions, in which the membrane potential has been measured electrophysiologically. The shift in membrane potential to this extent may occur from mechanoreceptive changes in K⁺ or Ca²⁺ conductance by about 1% and might be at the limit of electrophysiological measurement using membrane potential-sensitive dyes. Our measurements of propulsive velocity vs membrane potential also suggested that the reported propulsive force of Paramecium measured in a solution of graded densities with the aid of a video centrifuge microscope at 350 G was 11 times as large as that for −29 mV, i.e., the resting membrane potential at [K⁺]_o = 1 mM and [Ca²⁺]_o = 1 mM, and, by extrapolation, that Paramecium was hyperpolarized to −60 mV by gravity stimulation of 100- G equivalent, the value corrected by considering the reduction of density difference between the interior and exterior of the cell in the graded density solution. The estimated shift of the membrane potential from −29 mV to −60 mV by 100- G equivalent stimulation, i.e., 0.3 mV G⁻¹, could reach the magnitude entirely feasible to be measured more directly.     

电子环束流对航天器表面电位和等离子体鞘层的影响

采用二维三分量静电粒子模拟程序研究了电子环束流对低轨道磁化等离子体中运行的航天器表面电位和等离子体鞘层结构的影响.当有电子束流平行磁场入射时,航天器表面所带负电位的绝对值将增大.电子束流的速度和密度的增加将使航天器表面负电位绝对值增加很快.与此同时等离子体鞘层的尺度也将增大,形状将由向尾部延伸的“泪滴”状变成向两侧展开的“机翼”状.当电子环束流以相对于磁场成一定角度斜入射时,由于磁场的约束作用,航天器表面负电位的绝对值将随入射角增大而减小.      

落塔微重力水平激光干涉测量方法中的干扰因素分析

落塔是获得微重力环境的重要设施,落塔微重力水平的测量对微重力科学实验的研究至关重要. 激光干涉是测量落塔微重力水平的一种新方法,这种方法的基本原理是让一个参考落体在落舱中自由下落,落舱由于受到服外空气阻力的作用将与自由落体运动略有差异,1 11. 肫内的参考落体则更接近理想的自由落体运动,这就使得落舱与参考落体之间存在着加速度差,这种加速度差便反映了落服的微重力水平,其所导致的相对运动则可通过激光干涉的方法测量出来. 本文对落塔微重力水平的激光干涉测量方法中将会遇到的一些主要干扰因素进行了分析,计算结果表明,这些干扰网素所造成的总误差约为 1.2 x 10-7g,低于微重力水平的预测值 10-4~lO-6 g,因此该方法是一种比较可行的测量方法.      

Global value of Hubble constant

Multiaperture photometry in V (5500Å), r (6738Å) and IV (10500Å) of 52 spirals in nearby clusters Virgo, Fornax and Grus and farther clusters Cancer, Zw 74-23 and Peg I in the redshift range up to 6000 Km s⁻¹ was combined with HI width to derive three independant distances for each galaxy in these clusters.The plot between the mean distance of each cluster and its redshift, indicates the Hubble ratios of distant clusters Cancer, Zw 74-23 and Peg I are about 77 Km s⁻¹ Mpc⁻¹. Further, the Hubble ratios of distant clusters vary only from 76.3 to 78.9 Km s⁻¹ Mpc⁻¹ while those of nearby clusters Virgo, Fornax and Grus vary through a large range of 58.5 to 83.5 Km s⁻¹ Mpc⁻¹. We interpret these data by postulating a systematic motion toward Virgo for the Local Group.The best value for the global Hubble constant from farther and nearby clusters is derived as 74.3± 4 Km s⁻¹ Mpc⁻¹ and an average value of 289±60 Km s⁻¹ for the infall velocity of the Local Group toward Virgo is also derived.     

Heliospheric asymmetries due to the action of the interstellar magnetic field

We discuss the asymmetry of the heliospheric discontinuities obtained from the analysis of 3D modeling of the solar wind (SW) interaction with local interstellar medium (LISM). The flow of charged particles is governed by the ideal MHD equations and the flow of neutral particles is described by the Boltzmann equation. The emphasis is made on the asymmetries of the termination shock (TS) and the heliopause under the combined action of the interstellar and interplanetary magnetic fields (ISMF and IMF) in the presence of neutral hydrogen atoms whose transport through the heliosphere is modeled kinetically, using a Monte Carlo approach. We show that the deflection of neutral hydrogen flow from its original direction in the unperturbed LISM is highly anisotropic and evaluate a possible angle between the hydrogen deflection plane measured in the SOHO SWAN experiment and the plane containing the ISMF and LISM velocity vectors for different ISMF strengths. It is shown that the ISMF of a strength greater than 4 μG can account for the 10 AU difference in the TS heliocentric difference observed during its crossing by the Voyager 1 and Voyager 2 spacecraft, which however results in a larger discrepancy between the calculated and observed velocity distributions. The effect of a strong ISMF on the distribution of plasma quantities in the inner heliosheath and on 2–3 kHz radio emission is discussed.     

涡轮叶片尾缘复合通道隔板结构

采用热色液晶测温法测量涡轮叶片尾缘带隔板的复合通道的温度场.研究复合通道中3种不同形状的隔板对换热和流阻的影响.主要在矩形隔板、90°波形隔板、120°波形隔板3种结构之间进行换热和流阻的比较.结果表明:在本实验评价指标下,2种形状的波形隔板的换热均好于矩形隔板,而且相对较小的压力损失;90°隔板在第1通道换热上好于120°隔板,第2通道两隔板的换热基本相当,但是90°隔板相对有较大的压力损失.      

Launch and commissioning of the PAMELA experiment on board the Resurs-DK1 satellite

PAMELA is a satellite borne experiment designed to study with great accuracy cosmic rays of galactic, solar, and trapped nature in a wide energy range (protons: 80 MeV–700 GeV, electrons 50 MeV–400 GeV). Main objective is the study of the antimatter component: antiprotons (80 MeV–190 GeV), positrons (50 MeV–270 GeV) and search for antimatter (with a precision of the order of 10⁻⁸). The experiment, housed on board the Russian Resurs-DK1 satellite, was launched on June, 15th 2006 in a 350 × 600 km orbit with an inclination of 70°. The detector consists of a permanent magnet spectrometer core to provide rigidity and charge sign information, a Time-of-Flight system for velocity and charge information, a silicon–tungsten calorimeter and a neutron detector for lepton/hadron identification. An anticounter system is used off-line to reject false triggers coming from the satellite. In self-trigger mode the calorimeter, the neutron detector and a shower tail catcher are capable of an independent measure of the lepton (e⁺ + e⁻) component up to 2 TeV. In this work we focus on the first months of operations of the experiment during the commissioning phase.