FAST望远镜40米模型天文观测软件的开发

针对FAST的天文观测要求,对其天文观测软件进行了设计与开发。首先介绍了FAST天文观测的原理,对天文观测软件进行了需求分析。而后提出了馈源天文运动轨迹规划算法,并进行了仿真。针对其轨迹要求给出了控制方法,对天文观测控制软件进行了设计与实现。最后通过现场实地实验,验证了本文所提的算法与软件的可行性。     

多波段巡天和LAMOST观测目标

综述了国际上多波段巡天工作的进展。其中，x射线波段列举了至今主要的x射线卫星，特别介绍了ROSAT、ASCA、Chandra和XMM—Newton的情况；光学波段主要介绍了SDSS、DEEP以及2df的星系和类星体巡天；红外波段主要介绍了2MASS和SWIRE巡天；射电波段主要介绍了NVSS和FIRST巡天。根据光谱能力和观测模式，提出了LAMOST的选题目标，分析讨论了LAMOST可以开展的交叉证认工作。     

超导磁悬浮技术在南极望远镜中的应用

提出了超导磁悬浮望远镜的概念,建立了模型,提出了稳定悬浮方案,并用有限元软件对磁悬浮望远镜的磁场进行了三维静态分析,为南极望远镜水平轴系结构设计提供了新的思路.     

VLBI的SOLVK软件系统剖析及其某些改进

本介绍了VLBI的SOLVK软件系统的结构，并对其进行了三个方面的改进工作；1、编制了Make-Process程序；2、改进了CALC软件中的相对论时延；3、建立了残差件。     

新的不确定的天体力学——在空间动力学和天体力学国际讨论会上的主要演说

本文讨论了天体力学的不确定的特性,并探讨了它同稳定性研究的关系。当初始条件的不确定、未知的动力学影响以及不可积性同动力系统固有的不稳定性联接在一起时就产生了不确定性,结果,轨迹的集合就代替了单一轨迹,可靠的长期预报变成了不切实际的期望。确定性的问题成为使用经典的或数学的动力学模型的课堂练习,同时所有实际的问题却表现出不确定性来,而拉普拉斯的精神就不再适用了。木文首先定义了所使用的概念,列举了几个例子以说明不确定性的原因;然后讨论了与确定性有联系的稳定性。接着又探讨了不确定性的作用和几个重要的时间尺度。动力学系统的积分和变换的存在看来对确定性是有利的,但事实上它们仅仅延迟了剧烈变动的趋势。     

授时数据网络查询系统设计

为了满足用户简便地获取指定时刻和指定卫星的授时数据的需要,设计了基于互联网的授时数据查询系统,实现了系统对用户查询指令的自动回复。阐述了系统总体设计、软件的各组成模块及其实现。对系统进行了测试,结果表明系统达到了设计目的,验证了利用互联网进行授时数据查询的有效性。     

日像仪的电磁干扰分析

讨论了日像仪的干扰容限，列出了干扰源分布，估算出干扰测试仪灵敏度。计算了同步卫星干扰及干扰时间预测，也分析了中低轨道卫星干扰问题。对移动通信基站产生的干扰作了传播分析、计算，对脉冲雷达干扰作了谱分析及保守计算。     

恒星微波激射源

本文介绍了恒星微波激射源的基本分类。总结了恒星微波激射源的微波和红外发射的特点,并讨论了它们之间的相关。文中也简要介绍了恒星微波激射的动力学状态及抽运模型。最后提出了今后尚待解决的问题及初步打算。     

西藏星空之旅（下）

早上睡了一觉,我们就接着出发去珠峰大本营了! 一路颠簸,我们终于到达了大本营,就是有点失望,因为珠峰比想象中的要小。我们坐了25元／人的中巴来到了一号营地,这下离珠峰终于近了一些。本来商量说晚上要在这个一号营地通宵,幸好最后没有这样干,因为我们的装备并不支持,在大本营都已经很冷了。回到大本营后,我们还去踩了点,看看晚上要是拍摄哪里地景比较好。Jeff和小珊去了一个寺庙,我和子辉发现了结冰的河流。不一会儿,就开始下雪了。     

方兴未艾的红外天文学

本文阐述了红外天文学的重要性并介绍了目前红外天文所取得的一些初步成果。总结了我国红外天文工作的现状并对今后的发展提出了建议。     

SGP4/SDP4模型精度分析

本文基于最新发布的SGP4/SDP4(Simplified General Perturbation Version 4/Simplified Deep-space Perturbation Version 4)模型设计了一套定轨方案,从空间目标库中挑选出不同类型和轨道参数的1120个目标进行计算,定量给出了SGP4/SDP4模型处理不同类型空间目标的定轨预报精度.结果表明:近地目标定轨精度为百米量级;半同步和同步轨道定轨精度平均为0.7和1.9km.椭圆轨道目标的定轨精度与偏心率有关,除少数e>0.8的椭圆轨道目标,绝大多数椭圆轨道目标定轨误差均小于10km.用SGP4/SDP4模型对近地目标预报3天,半同步轨道预报30天,同步轨道预报15天,椭圆轨道预报1天,预报误差一般不超过40km.     

The Effect of GPS Ephemeris on the Accuracy of Precise Orbit Determination of LEO Satellite-borne GPS

The satellite-borne GPS receivers dedicated to precise orbit determination are now being carried by more and more low earth orbit (LEO) satellites and the satellite-borne GPS has become one of the main means for the precise orbit determination of low earth orbit satellites. The accuracy of satellite-borne GPS precise orbit determination depends on the accuracies of the GPS ephemeris and the clock error. Based on the orbit determination function of SHORDEIII zero-difference dynamics and using the observational data obtained by the GRACE satellites for the week from 2005 August 1 to 7 as an example, three versions of GPS ephemerides (igs, igr and igu) are used to carry out orbit determination under the same conditions and to estimate the effect of the GPS ephemeris accuracy on the accuracy of orbit determination of low earth orbit satellites. Our calculated results show that the two ephemerides, igs and igr, are equivalent to each other in orbit determination accuracy (about 9.5 cm), while igu is slightly less accurate, at about 10.5 cm. The effect produced by the data of the high frequency GPS satellite clock error on the accuracy of orbit determination is 1–6 cm.     

The Data Depth-weight-kernel Estimation of the Model Error of Satellite Orbit Determination

It is an objective fact that there exists error in the satellite dynamic model and it will be transferred to satellite orbit determination algorithm, forming a part of the connotative model error. Mixed with the systematic error and random error of the measurements, they form the unitive model error and badly restrict the precision of the orbit determination. We deduce in detail the equations of orbit improvement for a system with dynamic model error, construct the parametric model for the explicit part of the model and nonparametric model for the error that can not be explicitly described. We also construct the partially linear orbit determination model, estimate and fit the model error using a two-stage estimation and a kernel function estimation, and finally make the corresponding compensation in the orbit determination. Beginning from the data depth theory, a data depth weight kernel estimator for model error is proposed for the sake of promoting the steadiness of model error estimation. Simulation experiments of SBSS are performed. The results show clearly that the model error is one of the most important effects that will influence the precision of the orbit determination. The kernel function method can effectively estimate the model error, with the window width as a major restrict parameter. A data depth-weight-kernel estimation, however, can improve largely the robustness of the kernel function and therefore improve the precision of orbit determination.     

Determination of the parabolic orbit for a body moving in the plane of the ecliptic,by the Laplace method

A modification of the Laplace method for the determination of a preliminary orbit of a body moving in the plane of the ecliptic is presented. It is shown that on the basis of three close positions on the celestial sphere, the parabolic orbit can be determined in cases, when the classical Laplace method is not suitable. The numerical estimation of the number of possible solutions is carried out, and their spatial distribution depending on initial conditions is shown. An example of the determination of an orbit for the comet C/2007 N3 (Lulin) is given.     

On Methods for the Light Curves Extrema Determination

We present two methods for the determination of moments of extrema and their errors appropriate for the analysis of light variations of variable objects. The method I is suitable for determination of times of extrema of non-periodical variables or objects, whose light curves vary. The method II is apt for O-C analyses of objects whose light curves are more or less repeating. Both methods are displayed on the analysis of BL Cam light variations and compared with the Kwee-van Woerden method.     

基于CEI测量的GEO目标快速轨道恢复

连线干涉测量(Connected Element Interferometry, CEI)是一种全天时全天候的被动测角技术, 已用于空间目标的跟踪监视. 地球静止轨道(Geostationary Earth Orbit, GEO)卫星需要频繁机动以保持轨位或完成其他任务, 其机动后的快速轨道恢复能力对于监视预警极为重要. 针对基于CEI的GEO短弧定轨和预报, 分析了定轨算法的形亏和数亏, 在附加先验轨道约束的短弧定轨基础上, 提出了轨道半长轴初值的自适应优化方法. 利用亚太七号卫星的CEI仿真和实测数据进行了短弧定轨和预报, 实验结果表明, 采用优化后的半长轴初值, 30min短弧定轨和10min预报的卫星位置分量精度均优于4km, 能够满足非合作GEO目标机动后快速轨道恢复的需求.     

On the Laplacian orbit determination of asteroids

A modified Laplacian technique is described for initial orbit determination of asteroids from CCD observations and its applications for orbit determination of the main belt asteroids and near Earth asteroids. The proposed modification is based on a simultaneous improvement of both the orbital elements and the derivatives of spherical coordinates in frames of Laplace's method. It provides an orbit which represents the used observations with the residuals comparable with errors of these observations. The improved values of the derivatives might be used as ephemeris parameters for identification of newly discovered objects.     

Method for the determination of the distribution function for the mean frequency of supernova explosions

A method is suggested for the determination of the distribution function for the mean frequency of supernova explosions, which is similar to the Ambartsumian method for the determination of the distribution function for the mean flare frequency of flare stars. This method has not been applied because of the lack of the required data.Translated fromAstrofizika, Vol. 39, No. 4, pp. 561–566, November, 1996.     

On the inversion problem of the plasma line intensity measurements in terms of photoelectron fluxes

Assuming that the unidimensional distribution function of the photoelectron flux can be determined from plasma line intensity measurement, it is shown that the photoelectron flux distribution is not uniquely determined if additional hypotheses are not made. The limitations of the inversion procedure are shown: in particular, plasma line measurements cannot allow the determination of more than the first two Legendre components of the photoelectron flux. Experimental procedures for this determination are finally reviewed.