共查询到20条相似文献,搜索用时 341 毫秒
1.
本文对太阳射电高时间分辨率观测中的一些干扰问题作了初步分析,并提出了区分太阳射电精细结构事件与雷达干扰的相应办法。 相似文献
2.
射电望远镜具有极高的系统灵敏度,且系统内、系统间及台址内电子设备众多,电磁环境复杂,科学合理地评估台址内电子设备辐射发射对射电天文观测的影响,对系统电磁兼容性设计、无线电管理、屏蔽改造等有重要的指导意义。浅析了射电望远镜系统灵敏度及射电天文领域仪器设备辐射发射相关评估标准;基于射电望远镜系统灵敏度及观测需求,计算了南山25 m射电望远镜馈源口面干扰电平限值,并给出了天线旁瓣增益的计算方法;提出一种基于干扰电平限值、旁瓣增益、干扰测量、路径衰减的电子设备电磁辐射评估方法,并针对南山25 m射电望远镜天线驱动电磁辐射进行了评估,给出了屏蔽需求。 相似文献
3.
本文从资源卫星地面接收站选址的角度,考虑了对地面站允许干扰电平的规定。叙述了电磁干扰的分析计算的方法及实测方法,阐明了对测试系统的要求,以及就具体频谱仪及常见干扰源如何进行数据处理和带内干扰电平的归算等问题作了说明。本文提出的方法主要针对陆地卫星地面站,也可供其它人卫无线电观测站及微波接收站参考。 相似文献
4.
在天文观测中,射频干扰会造成假谱,降低数据的可靠性和有效性.射频干扰消减旨在减少干扰信号对射电天文观测的影响,包含器件方面的技术革新和数据处理领域的方法研究.针对德令哈13.7 m望远镜接收机中频部分引入的射频干扰,通过优化中频器件的抗射频干扰能力,提高了接收机的整体抗射频干扰能力,以主动消除方法来减少射频干扰耦合到接收机内部.分析了接收机干扰的传输路径,提出了器件射频干扰的直接耦合系数和器件射频干扰的系统耦合系数的概念,为定位干扰敏感器件并量化干扰引入比重提供了基础.经过抗射频干扰优化后,接收机抗干扰能力改善30 dB左右,望远镜的天文观测效率提高10%以上. 相似文献
5.
本文列举了云南天文台四波段太阳射电实测中得到的几种干扰实例及确认的太阳快速信号,在认识到太阳射电和干扰信号十分相似的基础上,探讨如何识别真伪信号问题。 相似文献
6.
关于太阳射电快速活动真伪信号识别问题 总被引:1,自引:1,他引:0
本文列举了云南天文台四波段太阳射电实测中得到的几种干扰实例及确认的太阳快速信号,在认识到太阳射电和干扰信号十分相似的基础上,探讨如何识别真伪信号问题。 相似文献
7.
随着频率使用率的提高, 射电天文台址地面或空间存在强电磁干扰致使望远镜接收机系统处于非线性状态. 为减少强电磁干扰的影响、提高天文观测效率, 提出了一种基于望远镜远场区域的强干扰源规避方法. 首先, 通过仿真分析确定的射电望远镜远场方向图, 结合望远镜与干扰源之间的位置关系, 分析了强电磁干扰到达射电望远镜焦点处的功率响应, 并依据接收机第2阶中频放大器性能参数, 确定射电望远镜处于非饱和状态的规避角度计算方法. 其次, 采用该方法计算分析了民航飞机对射电望远镜的影响, 若民航飞机上有主动发射的干扰源, 且不经过反射等传播现象, 当射电望远镜主波束轴偏开一定方向后, 可有效降低对射电望远镜的干扰强度. 相似文献
8.
从海量的天文观测数据中快速搜寻罕见的快速射电暴(Fast Radio Burst, FRB)事件, 干扰缓解是其中一项关键而具有挑战的工作. 射频干扰(Radio Frequency Interference, RFI)会淹没真实的天文事件, 还会导致搜寻管线输出大量的假阳性候选体. 由于干扰来源及其种类的复杂性, 目前并没有一种通用的方法可以解决这个问题. 为了降低干扰对FRB观测搜寻的影响, 分析和研究了南山26m射电望远镜L波段观测数据中的干扰情况, 针对主要的窄带干扰和宽带干扰建立了3层次的干扰缓解处理流程, 从而有效缓解了观测数据的干扰污染情况. 将该流程嵌入到FRB色散动态谱搜寻(Dispersed Dynamic Spectra Search, DDSS)管线中, 实验结果表明, 搜寻管线的检测率和检测精度得到了进一步的提高. 该方法为FRB观测数据干扰缓解处理提供了有价值的参考. 相似文献
9.
MSRT(密云综合孔径望远镜)从1985年起投入工作。在多年的观测中经常发现来自外部的强大干扰,严重影响着成图的质量。为了抑制观测过程中出现的各类干扰,我们发展了两种软件技术——剔除法和频域滤波法。滤波法的优点在于保留了全部观测信息,适合于长时间强干扰的情形。剔除法对脉冲形的干扰更为敏感有效。这两种技术的配合使用能有效、灵活地抑制各种不同干扰的影响。 相似文献
10.
在射电天文观测中,射频干扰(Radio Frequency Interference, RFI)会以多种形式混入望远镜接收系统,给观测带来误判或者降低观测信噪比.近年来国内国际射电天文快速发展,国内国际大型射电望远镜和阵列先后建设,观测灵敏度大为提高,射频干扰的影响尤为突出.随着科技发展和人类活动的加剧,射频干扰日益严重且不可逆转.提出利用2维离散小波变换的方法分析射电天文观测的数据,对望远镜系统输出的时间频率序列进行小波变换,根据小波系数分离出原始信号中各分量,每个分量统计得到相应的阈值,将各分量与阈值相比较识别干扰成分并标记去除.利用该方法对实际观测数据进行了处理,结果表明该方法能够很好地标记并消减干扰信号,且提高了观测的信噪比. 相似文献
11.
In the light of the problem of amalgamation and processing of multisource observational data in the combined orbit determination of near-earth satellites of the bi-satellite positioning system, the optimal weighting method of the improved variance component estimation of the two-step systematic error correction of homogeneous observational data is proposed. Analyses show that the multi-source amalgamation measurement model of the heterogeneous observational data essentially is a multi-structure, multi-parameter non-linear regression model, and the optimal weighting method of the combination of model structure characteristic analysis and variance component estimation of the heterogeneous observational data is established. The realization algorithms of the optimal weighting and the combined orbit determination parameter estimation of the two sorts of observational data are designed, and the simulation experiments of the combined orbit determination are carried out by taking the distances among the two satellites and the backup satellite and the homogeneous observational data and the distance between the two satellites and the heterogeneous observational data of satellite sensor angle measurements as the examples. The results of theoretical analysis and simulation calculation show that for the combined orbit determination of homogeneous observational data, the accuracy of orbit determination obtained by adopting the variance component estimation method of the two-step systematic error correction can be more superior than that obtained by means of the traditional empirical weighting method. For the combined orbit determination of heterogeneous observational data, through the introduction of the weighting factor by which the model structure is characterized the accuracies of the combined orbit determination of the near-earth satellite and geostationary satellite are both improved to a certain extent in comparison with the mean weighting mode. 相似文献
12.
13.
Peter Kammeyer 《Celestial Mechanics and Dynamical Astronomy》2000,77(4):241-272
This paper discusses a UT1-like quantity, UTGPS, determined daily from Earth-referenced GPS satellite orbits from the International GPS Service (IGS). For each satellite considered, the observed relation between the satellite's IGS orbit and a model of its orbit plane in inertial space is used to estimate UT1. This modeled orbit plane is initialized using the satellite's IGS orbit and the actual UT1 at an initial time. It is then propagated using standard models of gravitational forces and an empirical model representing the orbit-normal radiation pressure observed during several years of in-flight experience with the satellite. To estimate UT1, an a-priori transformation from terrestrial to true-of-date celestial coordinates is applied to the satellite's IGS orbit. The geocentric angular deviations of points of the resulting transformed orbit from the modeled orbit plane are analyzed, giving the angle between the ascending nodes of the satellite's transformed and modeled orbit planes. To this observed angle between nodes, converted to a UT1 difference, is added the a-priori UT1 value used in the transformation. From the result is subtracted a model of the angle, again converted to a UT1 difference, between the ascending nodes of the actual and modeled orbit planes. The final result is the estimate of UT1 from this satellite, and the median of the UT1 estimates from all satellites considered is UTGPS. The root-mean-square difference between UTGPS-UT1 at the beginning and at the end of an interval of one to four weeks is approximately 30 s times the square root of the interval's duration in weeks.This revised version was published online in October 2005 with corrections to the Cover Date. 相似文献
14.
15.
16.
17.
Luni-solar perturbations of an Earth satellite 总被引:1,自引:0,他引:1
A. E. Roy 《Astrophysics and Space Science》1969,4(4):375-386
Luni-solar perturbations of the orbit of an artificial Earth satellite are given by modifying the analytical theory of an artificial lunar satellite derived by the author in recent papers. Expressions for the first-order changes, both secular and periodic, in the elements of the geocentric Keplerian orbit of the earth satellite are given, the moon's geocentric orbit, including solar perturbations in it, being found by using Brown's lunar theory.The effects of Sun and Moon on the satellite orbit are described to a high order of accuracy so that the theory may be used for distant earth satellites. 相似文献
18.
利用全球卫星激光测距服务系统(ILRS,International Laser Ranging Service)标准点资料对Ajisai卫星进行精密定轨,残差均方根(RMS)优于3 cm,得到该星的精密轨道.进而对长春站40 cm空间碎片光电望远镜获得的Ajisai卫星的天文定位资料进行精度分析,外符合精度约3″左右.单独利用天文定位数据进行轨道改进,内符合精度优于3″.改进轨道的x、y、z坐标3分量在观测数据覆盖范围内的精度在100 m之内.同样地对Jason-1卫星作数据分析,结果和Ajisai卫星精度相当.分析各个弧段的精度变化,发现定标星个数减少,会导致天文定位精度下降.据此提出可以把最少定标星比例作为评定数据质量的参考指标之一. 相似文献
19.