磁选态单束铯束管铯原子速率分布的模拟计算

对铯炉准直器出口铯原子束的速率分布和角分布进行抽样,用蒙特卡罗方法模拟计算磁选态单束铯束管中五个关键位置的铯原子不同能级态的速率分布。结果是检测器处的铯原子速率分布不再符合麦克斯韦分布,分布密度最大值对应速率不随铯炉温度改变,只和束光学设计的参数有关。此模拟计算对指导磁选态铯束管束光学的设计有较大帮助。     

A study on radio-loud interacting/non-interacting CMEs-associated SEPs and solar flares

We have established a data set of 58 major hybrid SEP events associated with meter-to-decahectometer wavelength (m-to-DH) type II bursts, solar flares, and radio-load CMEs during the period of 1997–2014. The main focus of our study is to address the following two questions: Does the interaction of CMEs play a role in the enhancement of SEP intensity? Is there any difference in the seed population, and parent eruptions in the SEP events with and without CME interactions? Hence, the sample of 58 events is classified into two sets: (i) 35 non-interacting-CME-associated SEP events; (ii) 23 interacting-CME-associated SEP events. All the characteristics of SEPs, their associated CMEs/flares and the relationships between them are statistically analyzed and compared. Some of the basic attributes and relative elemental abundances (Fe/O ratios) of the both the sets are also compared. The results indicate that the seed particles in non-interacting-CME-associated SEP events are mostly from solar wind/coronal materials. But in the case of interacting-CME-associated SEP events, it may be associated with both flare material from preceding flares and coronal materials from solar wind/preceding CMEs. The correlation studies reveal that there are clear correlations between logarithmic peak intensity of SEP events and properties of CMEs (space speed: cc?=?0.56) and solar flares (peak intensity: cc?=?0.40; integrated flux: cc?=?0.52) for non-interacting-CME-associated SEP events. But these correlations are absent for the interacting-CME-associated events. In addition, the results suggest that interaction of primary CMEs with their preceding CMEs plays an important role in the enhancement of peak intensity of SEPs at least for a set of m-to-DH type II bursts associated SEP events.     

CFD simulation of helicopter rotor flow based on unsteady actuator disk model

Actuator Disks (AD) can provide characterizations of rotor wakes while reducing computational expense associated with modeling the fully resolved blades. This work presents an unsteady actuator disk method based on surface circulation distribution combined with empirical data, blade element theory and rotor momentum theory. The nonuniform circulation distribution accounts for 3D blade load effects, and in particular, tip loses. Numerical simulations were conducted for the isolated pressure sensitive paint model rotor blade in hover and forward flight using the HMB3 CFD solver of Glasgow University. Validation of CFD results in comparison with published numerical data was performed in hover, for a range of blade pitch angles using fully turbulent flow and the k-ω SST model. In forward flight, the vortex structures predicted using the unsteady actuator disk model showed configurations similar to the ones obtained using fully resolved rotor blades. Despite the reduced grid cells number, the CFD results for AD models captured well the main vortical structures around the rotor disk in comparison to the fully resolved cases.     

Interpretation of the SOHO/UVCS observations of two CME-driven shocks

We report on the analysis of two fast CME-driven shocks observed with the UltraViolet Coronagraph Spectrometer (UVCS) on board the Solar and Heliospheric Observatory (SOHO). The first event, detected on 2002 March 22 at 4.1 R_⊙ with the UVCS slit placed in correspondence with the flank of the expanding CME surface, represents the highest UV detection of a shock obtained so far with the UVCS instrument in the corona. The second one, detected on 2002 July 23 at 1.6 R_⊙ with the UVCS slit placed in correspondence with the front of the expanding CME surface, shows an anomalous deficiency of ion heating with respect to what observed in previous CME/shocks observed by UVCS, possibly reflecting the effect of different coronal plasma conditions over the solar cycle. From the two different sets of observations we derived an estimate for the shock compression ratio X, which turns out to be X = 2.4 ± 0.2 and X = 2.2 ± 0.1, respectively, for the first and second event. Comparison between the two events provides complementary perspectives on the dynamical evolution of CME-driven shocks.     

复杂群塔风荷载试验研究

介绍了一复杂群塔结构节段刚性测压试验概况和主要试验结果,讨论了结构典型部位风压分布的基本特征和结构风压分布的基本规律.试验结果表明,由于该结构由多个单体高耸塔结构组成,相互干扰严重,风压的分布相当复杂.根据风压试验结果得到了风力沿各塔高度的分布,并讨论了分布规律,进一步得出基底剪力系数和基底弯矩系数,分析了最危险风向,给出了用于结构设计的荷载建议.     

A new eclipsing low-mass X-ray binary with a giant companion

We detected hard X-ray emission from the unidentified Galactic bulge source 1RXS J175721.2-304405 with ASCA. The observed absorption column, flux and power-law index led us to consider that 1RXS J175721.2-304405 may be a new low-mass X-ray binary located near the Galactic center. Furthermore, the X-ray light-curve shows a step-function-like time variability, which is likely due to the occultation of a companion star. Future follow-up observations by missions such as ASTROSAT may reveal a periodic eclipse from 1RXS J175721.2-304405 if it is covered long enough. Since the long orbital period suggests a giant companion, follow-up observations will give firm evidence that 1RXS J175721.2-304405 is a new and rare eclipsing low-mass X-ray binary with a giant companion.     

考虑质心漂移的载人月面着陆器自适应姿态跟踪控制

月面着陆器在下降着陆过程中质量变化大,质心漂移及其引起的姿态扰动问题突出。载人月面着陆任务对安全性可靠性要求高,如何提高姿态控制的精度和稳定度是着陆任务顺利实施的关键。文章提出采用反作用控制系统和推力矢量控制的联合姿态控制方案,设计了自适应姿态控制器及质心漂移自适应估计器,通过李雅普洛夫方法证明闭环姿态控制系统稳定,引入反作用控制和推力矢量控制的误差特性以检验控制器的鲁棒性。数值仿真结果表明该控制方案可行,所设计自适应姿态控制器能使姿态控制系统稳定,推力矢量控制侧摆能使推力指向跟踪质心,可为工程应用提供参考。     

燃油分配对超燃冲压发动机的性能影响仿真分析

针对超燃冲压发动机两级燃油分配对内流道流动过程、燃烧模态、发动机性能及调节特性的影响问题,建立了发动机一维流动分析模型;对马赫数6/当量比1,马赫数6/当量比0.6,马赫数4/当量比1三种工况不同的一级/二级燃烧室燃油分配比例下的流动过程进行了仿真,并获得了不同燃油分配规律下的发动机性能.通过分析表明：超燃冲压发动机的两级燃油分配比例直接影响发动机内流道内的流动参数分布、燃烧模态及发动机比冲等性能参数.对于马赫数6/当量比1工况,当一级燃烧室的燃油分配比例为30％～70％时,可在全流道内组织纯超声速燃烧,最高比冲超过800 s;对于马赫数6/当量比0.6工况,即使将所有的燃油均在一级燃烧室喷入,流道也不会壅塞,该工况下最大比冲超过800s;对于马赫数4/当量比1工况,燃烧室内组织亚声速燃烧,最大比冲为1 031.9 s;为保证亚声速燃烧扰动不传递到燃烧室入口外,一级燃油分配比例不应过高.     

基于功率复用的椭圆球面波函数非正交调制方法

围绕如何降低基于椭圆球面波函数的非正交调制（PSWF-NPSM）系统误码率，降低信号检测复杂度，引入调制信号功率复用思想，提出基于功率复用的椭圆球面波函数非正交调制（PD-PSWF-NPSM）方法。该方法对载波信号按子波带进行功率分配，增加了调制信号最小欧式距离，降低了系统误码率；在接收端，提出基于检测统计量的串行干扰相消信号检测方法，依据不同支路信号间功率差异，对信号进行分离、检测。理论与仿真分析表明，该方法在不降低系统频带利用率、调制信号功率谱、峰均功率比特性前提下，能够有效提高系统误码性能，降低调制信号检测复杂度；与原非正交调制方法相比，当误比特率（BER）为10^-5时，所提方法系统误码性能提升约1.7 dB。     

燃烧室燃烧与排放特性试验与数值计算

为了探寻燃烧室进口空气温度、压力以及油气比对点熄火边界、温升、燃烧效率以及主要排放物摩尔分数的影响规律， 对航空发动机燃烧室在多工况下的点熄火特性、出口温度分布与主要排放物摩尔分数进行了试验测试。分别采用正癸烷的简化 反应机理与C 12 H 23 燃料的单步反应机理，对该燃烧室火焰筒内流场结构、温度场、中间组分与主要排放物摩尔分数分布特性进行了 数值计算，并与相应试验数据进行了对比分析。结果表明：随着燃烧室进口空气温度、压力以及油气比的提高，燃烧室燃烧效率、 温升、出口平均温度与NO X 摩尔分数逐渐提高，而UHC与CO摩尔分数逐渐降低；与采用C 12 H 23 燃料单步反应机理相比，采用正癸 烷的简化反应机理计算得到的火焰筒内流场与温度场分布更为合理，火焰筒出口温度场分布以及主要排放物摩尔分数与相应试 验数据更为接近，计算精度得到较大提高。