云台红外太阳望远镜中光电导行系统的像场旋转

红外太阳望远镜中的光电导行系统是高精度的反馈跟踪系统。在开环控制下,难以实现太阳望远镜的跟踪指标,所以必须使用光电导行作为目标位置反馈系统。但是在地平式系统跟踪过程中,光电导行望远镜中的像场会旋转,如果不进行消旋,光电导行系统就不能工作,这就需要解决光电导行系统中的像场旋转。本文在理论上分析了红外望远镜中光电导行系统的像场旋转,并给出了像在CCD面上的运动变化公式。     

云台红外太阳望远镜中光电导行系统的像场旋转

红外太阳望远镜中的光电导行系统是高精度的反馈跟踪系统。在开环控制下，难以实现太阳望远镜的跟踪指标，所以必须使用光电导行作为目标位置反馈系统。但是在地平式系统跟踪过程中，光电导行望远镜中的像场会旋转，如果不进行消旋，光电导行系统就不能工作，这就需要解决光电导行系统中的像场旋转。本文在理论上分析了红外望远镜中光电导行系统的像场旋转，并给出了像在CCD面上的运动变化公式。     

1m红外太阳望远镜光电导行系统中像场旋转的分析

云南天文台1m红外太阳望远镜(YNST)光电导行系统是基于检测太阳像在面阵CMOS图像传感器上的偏移量作为反馈控制信号的高精度闭环跟踪系统[1]。由于YNST是一个地平式装置,在太阳像偏移检测量中存在着像场旋转量,为了获取稳定清晰的太阳像,必须对检测量进行消旋[2]才能达到光电导行系统的跟踪要求。根据球面天文学及天体测量学的知识并结合导行镜的光学系统,推导了光电导行系统中像场旋转的变化规律并对其进行模拟分析。     

1m红外太阳望远镜光电导行系统的反馈控制分析

我国正在研制中的1m红外太阳望远镜是目前国内唯一的地平式真空太阳塔,主要用于活动区磁场的精细光谱分析和太阳活动区磁场的时空精细结构研究.要求望远镜必须长时间高精度跟踪太阳(0.3"/30s、1"/10min)才能实现它的科学目标.光电导行是实现望远镜高精度跟踪观测目标的关键控制技术,通过检测观测目标像在图像传感器上的移动量作为反馈控制信号对望远镜实行闭环控制.首先建立了光电导行系统的控制系统模型,然后分析了系统的稳定性能、暂态性能、时域特性、频域特性及跟踪性能,并采用PID控制器对系统进行优化设计,以提高光电导行反馈控制系统的稳定性和跟踪精度.通过计算机仿真设计,采用PID控制算法能实现1m红外太阳望远镜的跟踪要求.     

1米太阳望远镜光轴变化实测

针对1 m太阳望远镜导星镜光轴与望远镜光轴在跟踪过程中的相对变化对光电导行系统的影响,从数值模拟和实测两方面进行了深入分析.首先介绍1 m太阳望远镜及其光电导行系统的基本结构,并建立主镜镜筒的基本有限元模型,分析弯沉随镜筒指向高度的变化规律,模拟有弯沉存在时引入的跟踪误差及变化规律.然后根据该望远镜的系统结构,提出了望远镜光轴相对于导星镜光轴变化的实测方法.最后通过实测数据获得了望远镜光轴相对于导星镜光轴变化随镜筒指向高度的变化规律.     

FMG载荷地面试观测导行跟踪系统的设计与实现

全日面矢量磁像仪(Full-disk vector MagnetoGraph, FMG)是先进天基太阳天文台(Advanced Space-based Solar Observatory, ASO-S)卫星的3台主载荷之一,为开展FMG全系统性能测试和定标试验,已搭建用于FMG外场测试的地面试观测平台.利用该平台模拟FMG在轨跟踪状态,研制了基于全日面太阳图像的望远镜导行系统.该系统通过大面阵CCD (Charge Coupled Device)采集太阳像、多重逻辑条件判定、微调恒动跟踪速度校正偏移等策略,实现了RMS (Root Mean Square)优于1′′/30 min的跟踪精度.通过分析FMG方案阶段试观测的太阳纵向磁图,开启导行30 min后磁图特征点在赤经方向的偏移比恒动条件下减少17.5′′,提升了磁图空间分辨率.测试过程中该系统达到设计指标且工作稳定,为FMG地面试观测提供了良好的技术支撑.     

NVST的长期跟踪误差分析及改正

由于1 m太阳望远镜主体、光电导行及终端仪器消旋平台等的结构特点,即使光电导行系统闭环后,望远镜长时间跟踪精度仍然较低。为了解决这一问题,首先根据望远镜的结构特点分析了跟踪误差随时间变化的原因,然后通过理论和实测分析了误差的变化特点,研究了如何通过相关算法检测望远镜折轴焦点F_3焦面的高分辨率成像观测系统中的图像移动量,并平滑高频分量,分离出低频分量以反馈给望远镜定位跟踪系统,进一步提高望远镜的长时间跟踪精度。最后进行了高分辨率成像观测系统中TiO通道闭环跟踪实验,实验表明,在4小时的闭环跟踪时间内,跟踪误差的均方根值为0.52″,表明通过折轴焦点F_3成像观测系统中的图像移动量对望远镜实行闭环跟踪能够提高望远镜的长时间跟踪精度。     

全日面磁场与活动监测望远镜轴系升级

在天文观测中,需要望远镜能快速、准确地指向目标天体,并进行稳定跟踪。针对怀柔太阳观测基地(Huairou Solar Observing Station, HSOS)的全日面磁场与活动监测望远镜(The Solar Magnetism and Activity Telescope, SMAT)进行轴系升级,使用伺服电机轴上23位高精度绝对式编码器替代光栅钢带码盘,通过VSOP87行星理论实时计算日面中心位置,使用基于大面阵CCD的高精度导行系统不间断跟踪并记录太阳位置,利用最小二乘法分段拟合太阳实时位置与绝对式编码器数值,建立指向算法并实现日面中心指向。经实测,赤经方向的指向误差约为36.69″,赤纬方向的指向误差约为21.49″,满足全日面太阳磁场望远镜的指向要求,该方法成本低,兼容性高,对于其他赤道式望远镜的升级改造具有借鉴意义。     

YNST光电导行镜机械设计

YNST(云南1m太阳望远镜)光电导行系统的作用除了获取足够清晰的太阳像用作光电导行外,还参与望远镜光轴的校正.介绍了YNST光电导行镜的光学要求、机械设计结果及镜体设计所采用的被动无热化技术.校核了导行镜在阳光辐照下的热变形,计算了导行镜镜筒的最大弯沉,结果表明,所采用的无热化设计是有效的,导行镜刚度满足导行系统要求...     

太阳方位的自动获取及实时跟踪系统的设计

针对以往太阳方位手动计算复杂易错且不具备实时性的缺点设计了一套实时跟踪系统。该系统采用微芯公司生产的dsPIC作为核心处理器,具有处理速度快、功耗低的优点。系统结合了HMC3200电子罗盘与高精度视频方位仪,能够实时获取装置的位置指向和实时图像加以观察,使用的太阳方位算法简洁可操作性强、精度高,运行结果显示能满足实时追踪的效果。     

一种测定望远镜极轴偏差的方法

利用望远镜的恒动跟踪，对两颗恒星进行无斗星曝光０．５小时，扣除蒙气差影响，用球面三角方法计算出望远镜极轴指向的偏差在赤经和赤纬方向上的分量，据此对望远镜极轴进行调整，就可以方便地把望远镜极轴指向调整到较高精度。     

Acceleration feedback control(AFC) enhanced by disturbance observation and compensation(DOC) for high precision tracking in telescope systems

In this paper, a cascade acceleration feedback control(AFC) enhanced by a disturbance observation and compensation(DOC) method is proposed to improve the tracking precision of telescope systems.Telescope systems usually suffer some uncertain disturbances, such as wind load, nonlinear friction and other unknown disturbances. To ensure tracking precision, an acceleration feedback loop which can increase the stiffness of such a system is introduced. Moreover, to further improve the tracking precision, we introduce the DOC method which can accurately estimate the disturbance and compensate it. Furthermore,the analysis of tracking accuracy used by this method is proposed. Finally, a few comparative experimental results show that the proposed control method has excellent performance for reducing the tracking error of a telescope system.     

赤道式天文望远镜极轴调整分析及观测结果

天文望远镜的指向精度和跟踪精度是评判一架天文望远镜的重要指标。赤道式天文望远镜的指向精度和跟踪精度受到极轴位置准确性的影响。正确地安装好极轴位置显得非常重要。极轴校正是一项很重要的工作。介绍了用观测恒星的方法来校正极轴位置,分析了合理地选择目标恒星,得出结论:在调整极轴东西方向时选择子午圈上的恒星作为观测目标恒星,在调整极轴俯仰方向时选择90°时角圈上的恒星作为观测目标恒星。经过多次调整极轴东西方向和极轴俯仰方向并对两个方向交替进行调整,望远镜的极轴将处于相当准确的位置。     

Fast guiding and small telescopes in the 8-m era

Fast guiding may improve the images delivered by telescopes. It may be implemented fairly cheaply and offers an upgrade path to smaller telescopes, which will make them more useful in the 8-m era. However, the detailed performance of a fast guiding system must depend on many parameters and this makes it difficult to assess its precise scientific benefits. This paper provides a comprehensive mathematical framework for calculating the performance of fast guiding systems. A range of models has been calculated that illustrates the benefits for telescopes of various sizes in various wavelength ranges. Three measures of performance have been examined: FWHM, 50 per cent encircled energy diameter and energy concentration in a 0.35-arcsec aperture. Typical gains over natural seeing are found to be in the 20 to 40 per cent range at useful levels of sky coverage. Other things being equal, small telescopes do not benefit as much as large ones from fast guiding. The sensitivity of these benefits to assumptions has also been examined, and this highlights the need to operate in the correct wavelength range for the aperture in question. The largest perturbations to ideal models are likely to be the result of telescope windshake and the outer scale of turbulence. If there is appreciable windshake, fast guiding will yield larger benefits than expected from the natural seeing. A short outer scale (a few hundred metres) will, however, lose most of the gains.     

发生在1～2GHz的Ⅲ型爆发

对北京天文台动态频谱仪1996～1999年观测到的68群Ⅲ型爆发作了统计分析,并对这些事件的频率漂移、持续时间、偏振和带宽的基本特性作了定性分析.     

The design of the Central-Axis Reflector (ZAS)

The Central-Axis Reflector, the design principle which is presented below is a segmented-mirror telescope. The inventions relate mainly to the optical system and to the tracking apparatus.A large number of small individual mirror bodies, ground off-axis (hexagonal/polygonal) produce one primary mirror with closed circular aperture when joined together.The overall design of the tracking apperatus results directly —and thus without unnecessary adornment — from the two planes of to aminimum but which are required for tracking of the telescope.Paper presented at the Symposium on the JNLT and Related Engineering Developments, Tokyo, November 29–December 2, 1988.     

Automatic guiding of the primary image of solar Gregory telescopes

The primary image reflected from the field stop of solar Gregory telescopes is used for automatic guiding. This new system avoids temporal varying influences from the bending of the telescope tube by the main mirror's gravity and from offsets between the telescope and a separate guiding refractor. The required stiffness of the guider mechanics and the small areas of the sensors demand small f numbers for the guider optics, which cause problems with the image quality and with heat. Problems also arise from the pinhole in the telescope's field stop which is imaged as a dark dot on the sensor. Pointing errors introduced by the telescope affect shifts of the solar image on the sensor. These are numerically determined by Fourier methods which are found to be less sensitive to noise than profile centering methods. Several types of guiders are tested, the final equipment, now installed at the Gregory telescopes at Tenerife and at Locarno, is described.     

An improved astrometric calibration technique for space debris observation

An optical survey is the main technique for detecting space debris. Due to the specific characteristics of observation, the pointing errors and tracking errors of the telescope as well as image degradation may be significant, which make it difficult for astrometric calibration. Here we present an improved method that corrects the pointing and tracking errors, and measures the image position precisely. The pipeline is tested on a number of CCD images obtained from a 1-m telescope administered by Xinjiang Astronomical Observatory while observing a GPS satellite. The results show that the position measurement error of the background stars is around 0.1 pixel, while the time cost for a single frame is about 7.5 s; hence the reliability and accuracy of our method are demonstrated. In addition, our method shows a versatile and feasible way to perform space debris observation utilizing non-dedicated telescopes, which means more sensors could be involved and the ability to perform surveys could be improved.