边带分离型超导SIS接收机本振耦合噪声研究

超导SIS (Superconductor-Insulator-Superconductor)接收机因极低的接收机噪声温度成为毫米波和亚毫米波段射电天文观测的首选.本振系统耦合噪声也是接收机噪声的一部分,在多年的天文观测中,发现本振耦合噪声无法完全忽略,对天文观测的灵敏度有一定影响.采用两个不同种类的信号发生器作为本振系统初级信号源,测试了超导SIS接收机的噪声温度,发现信号发生器输出的基底噪声能够耦合到接收机内部,从而增加接收机噪声强度.分析研究了本振系统热噪声和信号发生器基底噪声对接收机噪声的影响.通过在信号发生器输入端加入窄带滤波器滤除其基底噪声,消除了信号发生器基底噪声引入的接收机噪声,降低了接收机的整体噪声,提高了望远镜的灵敏度.     

基于分布式控制的天线闭环控制系统设计和实现

给出了天线阵列系统中单天线闭环控制系统的模型,对于同步跟踪某种信号源进行射电天文观测的天线阵列系统而言,具有通用性、可配置性和良好的可扩展性.     

应用于射电天文的低噪声温度测量方法

噪声温度是接收机和低噪声放大器最重要的性能指标,是了解设备性能好坏的关键因素。随着电子技术的快速发展,接收机和低噪声放大器的噪声温度变得越来越低,准确而快速地测量接收机和低噪声放大器的噪声温度变得非常困难。介绍了6种在射电天文中经常使用的测量低噪声温度的方法,这些测量方法具有准确可靠、简单易行的优点。叙述了测量原理并给出了一些测量方法的测量结果,对影响测量噪声温度精度并且易被忽视的因素也做了详细讨论。     

TM65m射电望远镜L、S、C、X频段天线性能测量

报告了上海天马65 m射电望远镜(简称TM65m)4个低频(L、S、C、X)段的天线效率、灵敏度以及系统噪声温度的性能测试情况.首先介绍了射电天文接收系统的关键指标,接着对测试方法进行了论述,并对误差进行了评估.最后给出了TM65m上4个低频段的天线效率、灵敏度以及系统噪声温度的测试情况,测试结果表明:在C和X波段,副面位置固定时,在高低俯仰角上效率和灵敏度下降剧烈,当启动副面(随动)模型后,在全仰角范围内,效率可以控制到60%以上.系统噪声温度与副面模型无关,在4个波段中C波段的灵敏度和系统噪声温度最佳.     

精确时延补偿的自适应旁瓣相消射电抗干扰方法研究

导航信号作为射电干扰信号影响L波段射电观测时,与雷达、通信领域的干扰不同,其功率通常小于噪声功率,使得利用干扰信号相关性的传统抗干扰方法效果不佳,且缺乏有效的评价指标。针对以上问题,依据射电信号处理流程构建了射电抗干扰系统框架,并从射电观测数据应用出发,给出了干扰抑制度和信号损失度两个指标。同时提出在精确补偿时延后利用抑制干扰子空间噪声分量的自适应旁瓣相消方法来消除导航信号的影响;仿真结果表明,本方法能有效抑制导航信号对射电观测的影响,且性能优于传统基于特征子空间的自适应旁瓣相消方法。     

射电天文30～300 MHz频段稀布阵列关键技术分析与研究

30～300 MHz的甚高频(Very High Frequency, VHF)频段是重要的射电天文波段,该频段观测采用天线阵组阵方式。稀布阵列具有空间分辨率高、副瓣电平低以及造价低等优点,进一步的天线阵综合加权可以对天线阵主瓣波束进行有效赋形,对最大旁瓣副瓣(Maximum Side Lobe)电平和远区栅瓣(Far Side Lobe)电平进行抑制。首先回顾了射电天文甚高频稀布阵列研究发展和现状,以及将会遇到的难点,提出了首先优化最优稀布天线阵元排布,进一步提出融合高性能计算平台+FPGA SOPC的稀布甚高频射电天文阵列信号处理结构体系,在图形处理器(Graphics Processing Unit, GPU)或者云计算平台上完成对天线阵各阵元频点加权参数的计算,然后通过高速总线将计算参数下发到前端的信号处理板中,通过FPGA SOPC完成对加权参数的配发。进一步分析计算了多波束情况下的数据率,可以实现实时的参数配置。本文成果为下一步大规模甚高频天线阵架设提供了技术依据。     

风云二号气象卫星地面站天线射电天文测量系统

本文描述了风云二号气象卫星地面站天线射电天文测量系统以及用射电天文方法进行天线参数测量的硬件和软件。     

基于斩波轮技术的K波段接收机噪声校准研究

接收机是射电天文中用于探测微弱射电信号的重要接收设备.接收机的强度校准就是将接收机对射电源的响应转换为天文意义上的流量密度.常规方法就是使用经典的冷热负载法,将接收机自身的强度响应转换为一个等效的温度值,之后再据此对射电源做进一步标定.通过搭建基于斩波轮技术的K波段接收机强度校准平台,使用斩波轮法测试K波段常温接收机的噪声温度,并与传统冷热负载法的测试结果进行比对.结果显示,在晴好天气条件下,斩波轮法在30°、90°仰角下噪声温度的最大测试误差为7.5%和8.4%,可以很好地应用于实际噪声温度测试中;但在5°仰角测试中,由于过低仰角引入了地面噪声,使得斩波轮法的测试误差上升至20%–30%之间而无法使用.希望在此基础上进一步开展K波段天空亮温度的理论计算与实测,从而完善斩波轮技术的应用,使之可以满足在不同气象条件下的噪声校准测试需求.     

德令哈13.7m望远镜多波束接收机的运行

德令哈13.7 m望远镜是中国最重要的射电望远镜之一.望远镜自安装超导成像频谱仪以及采用飞行观测模式以来,运行近10 yr.在此期间,望远镜开展并完成大量的天文观测,累积了巨量的天文数据,取得了一系列重要的科研成果.介绍了超导成像频谱仪在天文观测中的运行状态,运行中疑难问题、故障现象及解决方案.详述了超导成像频谱仪各方面性能测试及多年来的性能分析,包含接收机噪声温度及望远镜系统噪声温度、镜像抑制比、接收机稳定性、波束性能等方面.列举了超导成像频谱仪更新发展方面的工作,包含本振功率自动化调整、边带分离型超导混频器预放大电路的更新、控制程序的优化等.总结经验和规律,承前启后,将过去的超导成像频谱仪的维护运行经验应用到之后新一代大规模接收机系统中.     

基于100 nm砷化镓pHEMT工艺的C波段宽带低噪声放大器芯片

作为射电天文接收机系统的关键器件, 低噪声放大器的噪声和增益性能对接收机系统的灵敏度有重要影响. 采用100nm砷化镓赝配高电子迁移率晶体管(pseudomorphic High Electron Mobility Transistor, pHEMT)\lk工艺, 研制了一款可覆盖C波段(4--8GHz)的低噪声放大器(Low Noise Amplifier, LNA). 所设计的LNA采用3级共源级联放大拓扑结构, 栅极、漏极双电源供电. 常温下测试表明, 该LNA在4--8GHz频段内平均噪声温度为\lk60K, 在5GHz处获得最低噪声温度50K, 通带内增益($31\pm1.5$)dB, 输入输出回波损耗均优于10dB, 芯片面积为$2.1\times1.1$mm², 可以应用于C波段射电天文接收机以及卫星通信系统等.     

Acceleration of Numerical Integration of the Equations of Motion of Asteroids

Solar System Research - Finding and studying possible collisions of asteroids approaching the Earth requires a significant amount of computation. This paper describes the R0 program created to...     

Equation of state and anisotropy of pressure of magnetars

Magnetars are the neutron stars with the highest magnetic fields up to 10¹⁵–10¹⁶ G. It has been proposed that they are also responsible for a variety of extra-galactic phenomena, ranging from giant flares in nearby galaxies to fast radio bursts. Utilizing a relativistic mean field model and a variable magnetic field configuration, we investigate the effects of strong magnetic fields on the equation of state and anisotropy of pressure of magnetars. It is found that the mass and radius of low-mass magnetars are weakly enhanced under the action of the strong magnetic field, and the anisotropy of pressure can be ignored. Unlike other previous investigations, the magnetic field is unable to violate the mass limit of the neutron stars.     

Observations of the intensity of the penumbra of sunspots

Observations of the penumbral intensity of sunspots in 13 wavelength regions are presented. In 4 wavelength regions 54 sunspots are measured. In the other wavelength regions the number of sunspots considered ranges from 3–19.The penumbral intensity alters with position within the spot. This intensity variation is found to be comparable with the change in intensity from one spot to another. The penumbral intensity is found to be independent of spot size in the sample considered.The penumbra model of Kjeldseth Moe and Maltby (1969) with = 0.055 is supported by the measurements.     

A survey of orbits of co-orbitals of Mars

Many asteroids with a semimajor axis close to that of Mars have been discovered in the last several years. Potentially some of these could be in 1:1 resonance with Mars, much as are the classic Trojan asteroids with Jupiter, and its lesser-known horseshoe companions with Earth. In the 1990s, two Trojan companions of Mars, 5261 Eureka and 1998 VF₃₁, were discovered, librating about the L₅ Lagrange point, 60° behind Mars in its orbit. Although several other potential Mars Trojans have been identified, our orbital calculations show only one other known asteroid, 1999 UJ₇, to be a Trojan, associated with the L₄ Lagrange point, 60° ahead of Mars in its orbit. We further find that asteroid 36017 (1999 ND₄₃) is a horseshoe librator, alternating with periods of Trojan motion. This asteroid makes repeated close approaches to Earth and has a chaotic orbit whose behavior can be confidently predicted for less than 3000 years. We identify two objects, 2001 HW₁₅ and 2000 TG₂, within the resonant region capable of undergoing what we designate “circulation transition”, in which objects can pass between circulation outside the orbit of Mars and circulation inside it, or vice versa. The eccentricity of the orbit of Mars appears to play an important role in circulation transition and in horseshoe motion. Based on the orbits and on spectroscopic data, the Trojan asteroids of Mars may be primordial bodies, while some co-orbital bodies may be in a temporary state of motion.     

Graphical representation of periodic motion of the line of nodes of the Moon

In the text-books of astronomy, sections generally related to the Moon deal with the orbital elements of the Earth-Moon system such asa, e, i, , and the time of perigee passage. While the MEAN of the first of the three elements do not vary, mean longitude of the ascending node-mean longitude of the lunar perigee and the time of perigee passage undergoes secular as well as periodic changes due predominantly to the action of the Sun's gravitational attraction. While to a certain degree, explanations related to the calculation of the lunar orbit parameters are given, not a single graphical representation of these short- or long-periodic changes are presented. We allow the number of data related to these periodic changes must cover a large span of time; and if regression of the line of nodes or advances of the line of apses are to be graphically seen, data covering 18.61 and 8.85 yr, respectively, are needed. In this work we particularly aim at the graphical representation of the periodic changes of the line of nodes.