风洞试验中风剖面的模拟及近流场特性分析

首先简单介绍了日本东京工艺大学风工程研究中心新建的开环流低速边界层风洞中风剖面模拟的试验情况.基于试验结果,采用被广泛应用的三角尖劈加上布置粗糙元的方法,成功地模拟出日本建筑学会定义的四类不同场地对应的风剖面.通过对试验数据的比较分析,就所采用的立方体粗糙元及三角尖劈对最终模拟得到的风剖面特性的影响进行了比较分析.其次,对风剖面模拟及特性判定中的几个重要问题,如三角尖劈的形状优化、风速功率谱的一致性、积分尺度的分析方法等进行了分析.最后,基于以上分析,对在边界层风洞中模拟预定的风剖面提出几点参考意见.     

环境激励条件建筑结构的试验建模研究

通过环境激励模态识别技术对一座中高层新结构大楼环境激励试验建模研究。首先介绍了试验模型设计 ,并在现场测量整栋大楼在环境激励下的振动响应。然后采用新发展的频率空间域方法 ( FSDD)进行模态识别 ,分别在 0～ 4.5 Hz和 0～ 6.5 Hz频率范围识别出 9阶弯曲和扭转模态频率和振型。采用频率空间域方法识别了结构的阻尼特性 ,并得到满意的结果。所得试验模型已成功应用于 CFT大楼的有限元动态模型修正。所研发的试验建模技术可望在结构响应预报 ,健康监测和振动控制中发挥重要作用     

XMM-Newton study of soft excess X-ray emission in clusters of galaxies

We discuss the detection of soft excess X-ray emission in a sample of 19 clusters of galaxies observed by XMM-Newton. In 6/19 clusters evidence for a soft X-ray excess is found. Four of these clusters show soft X-ray and O VII line emission from gas with a temperature of 0.2 keV. The centroid of this oxygen line is consistent with the redshift of the cluster. The intensity and spatial extend of the soft excess agrees with previous PSPC measurements. These observations are interpreted as emission from warm-hot intergalactic medium filaments, with density enhancements near the cluster centers, consistent with theoretical predictions. In the other two soft excess clusters a non-thermal origin is consistent with the data.     

ETS-II Experiments Part II: Earth Station Facilities

A part of the Earth station at the Kashima Branch of the Radio Research Laboratories has a highly sensitive receiving system newly designed for receiving 3 coherent and weak beacon signals transmitted from the Engineering Test Satellite Type-II (ETS-II) of Japan and obtaining propagation data on quasimillimeter and millimeter wavelengths. The ground system includes a main receiving station which has a 10-m diameter antenna for multifrequencies, highly sensitive receivers, a rain radar, which has many unique functions, a radiometer, meteorological instruments, and data processing computers. The facilities of the main receiving station for ETS-II propagation experiments, except for the rain radar, are described.     

Detached-Eddy Simulation方法模拟不同类型翼型的失速特性

 应用DES(Detached-EddySimulation)方法数值模拟了3种不同失速类型的翼型的升力特性。DES方法结合了RANS(Reynolds-averagedNavier-Stokes)和LES(LargeEddySimulationapproaches)的优点。基于Spalart-Allmaras湍流模型,在近壁面DES体现为RANS模型的特点而在远离物面处又具有LES的亚格子模型的特性。对此模型使用了LU-SGS隐式格式求解。通过和实验结果对比,显示这种方法可以有效地预测翼型的失速特性。     

A space station experiment on large antenna assembly and measurement

The large assembly antenna in space can meet future requirements of both high frequency and large aperture. This paper proposes an experiment on assembling a large antenna at the Space Station, and discusses a realizable procedure of the experiment. The objective of this experiment is that a large antenna of a 10-m diameter is assembled in space and at the same time problems occurring in the assembling process are clarified by conducting the following experiments: assembly of test articles by manipulators, measurement of both mechanical and electrical performance of the assembled antenna, test of the pointing control system, and operational test. In the operational test, the weather radar development test and the large aperture microwave radiometer development test are conducted. Furthermore, the problem areas and items of further study are discussed in this paper.     

A challenge to the highest balloon altitude

Development of a balloon to fly at higher altitudes is one of the most attractive challenges for scientific balloon technologies. After reaching the highest balloon altitude of 53.0 km using the 3.4 μm film in 2002, a thinner balloon film with a thickness of 2.8 μm was developed. A 5000 m³ balloon made with this film was launched successfully in 2004. However, three 60,000 m³ balloons with the same film launched in 2005, 2006, and 2007, failed during ascent. The mechanical properties of the 2.8 μm film were investigated intensively to look for degradation of the ultimate strength and its elongation as compared to the other thicker balloon films. The requirement of the balloon film was also studied using an empirical and a physical model assuming an axis-symmetrical balloon shape and the static pressure. It was found that the film was strong enough. A stress due to the dynamic pressure by the wind shear is considered as the possible reason for the unsuccessful flights. A 80,000 m³ balloon with cap films covering 9 m from the balloon top will be launch in 2011 to test the appropriateness of this reinforcement.     

High-speed unsteady flows past two-body configurations

This paper presents a detailed investigation of unsteady supersonic flows around a typical two-body configuration, which consists of a capsule and a canopy. The cases with different trailing distances between the capsule and canopy are simulated. The objective of this study is to examine the detailed effects of trailing distance on the flow fields and analyze the flow physics of the different flow modes around the parachute-like two-body model. The computational results show unsteady pulsating flow fields in the small trailing distance cases and are in reasonable agreement with the experimental data. As the trailing distance increases, this unsteady flow mode takes different forms along with the wake/shock and shock/shock interactions, and then gradually fades away and transits to oscillate mode, which is very different from the former. As the trailing distance keeps increasing, only the capsule wake/canopy shock interaction is present in the flow field around the two-body model, which reveals that the unsteady capsule shock/canopy shock interaction is a key mechanism for the pulsation mode.     

Progress of super-pressure balloon development: A new “tawara” concept with improved stability

The super-pressure balloon (SPB) has been expected to be a flight vehicle that can provide a long flight duration to science. Since 1997, we have developed the SPB. Now we are at the phase of developing an SPB of a practical size. In 2009, we carried out a test flight of a pumpkin-shaped SPB with a 60,000 m³ volume. The undesirable result of this flight aroused us to resolve the deployment instability of the pumpkin-shaped SPB, which has been known as one of the most challenging issues confronting SPB development. To explore this deployment issue, in 2010, we carried out a series of ground tests. From results of these tests, we found that an SPB design modified from pumpkin, named “tawara”, can be a good candidate to greatly improve the deployment stability of the lobed SPB.