CSRm束流累积阶段闭轨校正系统设计

为测量兰州重离子加速器冷却储存环主环(CSRm)束流累积阶段的闭轨畸变并进行闭轨校正,开发了闭轨校正系统,该系统由轨道测量系统、闭轨控制系统和校正磁铁系统构成。轨道测量系统实现对束流轨道的实时监测;闭轨控制系统读取束流轨道信息,然后进行闭轨校正计算,并将计算后的校正值传输给校正磁铁系统;校正磁铁系统通过改变校正电源的值,改变校正磁铁的强度,实现对束流轨道的调整,完成闭轨校正。模拟测试结果表明,束流轨道水平方向的最大畸变由校正前的3.37 mm减小为校正后的0.39 mm,垂直方向的最大畸变由校正前的4.21 mm减小为校正后的0.31 mm。该系统能够实现响应矩阵的自动测量和束流轨道的自动校正,满足设计要求。     

合肥光源束流闭轨局部调整和校正

 针对特定实验站调整光源点位置的要求,设计了合肥光源储存环束流闭轨局部调整和校正系统,介绍了该系统的工作原理、硬件组成、软件设计及运行结果,设计要求束流闭轨局部调整的最大幅度为1~2 mm,水平方向和垂直方向其余闭轨畸变均方根分别小于50和30 μm。校正系统采用轨道设定法作为束流闭轨局部调整和校正算法,由束流轨道测量系统、校正铁系统和控制系统组成。运行结果显示：水平和垂直方向分别调节2.0和1.5 mm,水平方向和垂直方向其余闭轨畸变均方根分别为45.14和27.62 μm。     

利用约束线性最小二乘法实现合肥光源束流闭轨全环校正和反馈

由于存在各种非理想因素,束流在储存环中的闭轨会发生畸变。对束流闭轨畸变进行校正的方法较多,目前合肥光源(HLS)采用奇异值分解(SVD)法进行束流闭轨的全环校正和反馈。针对SVD法不足之处,采用约束线性最小二乘法(CLLS)来改进HLS束流闭轨的全环校正和反馈。介绍了束流闭轨畸变校正的理论,着重介绍应用CLLS对HLS储存环束流闭轨畸变进行全环校正和反馈,并给出运行结果。结果显示,利用CLLS后,HLS敏感实验线站的束流轨道稳定性和重复性得到明显改善。     

上海光源储存环轨道噪声分析

利用上海光源束流位置测量系统Libera电子学对储存环轨道数据进行了测量,分析了Libera对束流位置测量系统探头信号的处理过程,应用MATLAB软件对数据进行了处理,采用Welch方法对轨道噪声数据进行了功率谱和积分功率谱分析,获得了主要噪声源的相关信息,为消除噪声、提高轨道稳定性提供了依据。实验结果表明:在储存环的不同位置,噪声功率谱的结构具有相似性;尽管不同频段噪声对功率谱影响不同,但是噪声源主要来自于低频段的地基振动、支架共振和磁铁电源。     

有机化合物电子光谱中的助色基及其作用机理探讨(Ⅱ)

助色基的未成键电子对与生色基的最低π~*反键轨道和最高π成键轨道线性组合成三个新的分子轨道。其中能量最高的π~*是反键轨道,它的能量一定高于原生色基的π~*轨道;最高占据π轨道的能级与原生色基的π轨道相比,孰高孰低将随生色基和助色基的不同而异;原生色基的n轨道与助色基的未共用电子对所占轨道相互正交,故两者间的作用可忽略不计,n轨道能级基本保持不变。因此助色基使生色基的n→π~*跃迁吸收波长发生蓝移,而π→π~*跃迁吸收波长是红移还是蓝移,则随生色基及助色基的不同而异。     

人造卫星相对论中间轨道的积分

由于激光技术可使人造卫星轨道测量精度大大提高,因此轨道计算必须考虑广义相对论效应.本文将中间轨道理论推广到考虑广义相对论效应的人造卫星轨道计算中,给出了相对论中间轨道的积分,并导出了以轨道参数为变量的相对论摄动运动方程.     

基于MATLAB的合肥光源储存环束流轨道校正系统

 闭轨畸变对合肥同步光源的束流质量产生负面影响，因此必须对闭轨畸变进行校正。本文介绍了基于MATLAB的合肥光源储存环束流轨道校正系统的工作原理、开发过程及测试结果。该系统由束流轨道测量系统、校正铁系统和控制系统组成，基于MATLAB开发的束流轨道校正程序运行于操作员界面工作站上。首先对获取的束流轨道数据进行分析和计算，然后通过控制系统改变校正铁电源的电流以改变校正铁磁场强度，从而实现轨道校正。测试结果表明：束流轨道的最大畸变由校正前的4.468 mm下降到校正后的0.299 mm；标准方差（SDEV）由校正前的2.986 mm下降到校正后的0.087 mm。该系统达到了设计目标。     

托卡马克装置中高能离子的直接损失

通过严格求解导心坐标系下的哈密顿方程,提出了托卡马克装置中离子的真实轨道理论,并利用此理论对国际热核聚变实验堆(ITER)中α离子的真实轨道进行了数值模拟研究,获得了驻点轨道和近期理论预言的半俘获轨道.根据此真实轨道理论计算了ITER中α离子的直接损失率.结果发现,与所提出的真实轨道理论相比,以前的回旋平均理论大幅度低估了α离子的直接损失率,两种理论的损失率差值可达14%,对此差异进行了详细的分析并给出了物理上的解释.     

太阳同步圆轨道空间相机瞬态外热流计算

为了使空间相机热设计、热分析、热试验具备准确、可靠的热边界条件,对太阳同步圆轨道空间相机的瞬态外热流进行了计算。总结了卫星空间定位的6个轨道根数之间的关系,给出了太阳同步圆轨道空间定位的必要参数。针对某给定太阳同步圆轨道,采用STK软件进行了轨道面与太阳光矢量相对位置关系（β角）的计算,确定了该轨道的高、低温工况位置。归纳了空间外热流的理论计算方法,以外接于卫星平台的空间相机为例,建立了外热流计算模型,采用IDEAS/TMG模块对给定太阳同步圆轨道的高、低温工况轨道周期内瞬态外热流变化进行了分析计算,得出了太阳辐射热流、地球太阳反照热流、地球红外辐射热流在轨道周期内的详细变化曲线,得到的结果可以作为空间相机热设计、热分析及地面热试验外热流模拟的输入条件。     

A new method for orbit determination: Unit vector method

In this paper, a method of orbit determination is presented according to the principle of unit vector method (UVM). The model and arithmetic are improved and it not only suits initial orbit determination with short arc data, it also suits orbit improvement with data longer. It is also suitable for orbit of any eccentricity and any inclination. It omits most partial derivatives of all the elements which must be calculated in classical differential orbit improvement (DOI), so, it is more efficient than DOI, and the accuracy of orbit determination and convergence of algorithm are also improved appreciably.     

载人登月转移轨道偏差传播机理分析与稳健性设计

载人登月转移轨道具有飞行时间长, 动力学模型复杂, 非线性强且变系数的特点, 而载人登月工程对转移轨道可靠性要求极高, 研究地月转移轨道偏差传播机理和轨道稳健性设计不仅具有工程意义, 更具有探索地月空间复杂引力场对轨道偏差作用的科学意义. 本文首先分析了日地月中心引力和地球J₂项摄动等主要作用力对转移轨道偏差的作用范围与影响大小, 其次提出了一种基于标称轨道数据的变系数非线性动力学系统偏差传播机理解析分析方法, 最后构建了基于偏差传播矩阵的转移轨道稳健性评价指标, 并基于NSGA-II (Nondominated Sorting Genetic Algorithms)算法求解了载人登月转移轨道稳健性优化设计问题. 仿真结果表明, 本文提出的偏差传播机理分析方法能快速准确地求解出载人登月转移轨道偏差传播矩阵, 利用偏差传播矩阵进行协方差分析和中途修正脉冲计算是简单准确的, 考虑稳健性的转移轨道优化设计可以提高标称轨道品质. 关键词： 载人登月 转移轨道 偏差分析 稳健性设计     

Methods of rapid orbit forecasting after maneuvers for geostationary satellites

A geostationary (GEO) satellite may serve as a navigation satellite, but there is a problem that maneuvers frequently occur and the forces are difficult to model. Based on the technique of determining satellite orbits by transfer, a predicted orbit with high accuracy may be achieved by the method of statistical orbit determination in case of no maneuver force. The predicted orbit will soon be invalid after the maneuver starts, and it takes a long time to get a valid orbit after the maneuver ends. In order to improve ephemeris usability, the method of rapid orbit forecasting after maneuvers is studied. First, GEO satellite movement is analyzed in case of maneuvers based on the observation from the orbit measurement system by transfer. Then when a GEO satellite is in the free status just after maneuvers, the short arc observation is used to forecast the orbit. It is assumed that the common system bias and biases of each station are constant, which can be obtained from orbit determination with long arc observations. In this way, only 6 orbit elements would be solved by the method of statistical orbit determination, and the ephemeris with high accuracy may be soon obtained. Actual orbit forecasting with short arc observation for SINOSAT-1 satellite shows that, with the tracking network available, the precision of the predicted orbit (RMS of O-C) can reach about 5 m with 15 min arc observation, and about 3 m with 30 min arc observation. Supported by the National High Technology Research and Development Program of China (Grant No. 2006AA12Z322), the National Basic Research Program of China (Grant No. 2007CB815503), and the West Light Program of Chinese Academy of Sciences (Grant No. 2007LH01)     

有机化合物电子光谱中的助色基及其作用机理探讨(Ⅰ)

本文就电子光谱中助色基的作用进行了讨论 ,认为不能一概地认为助色基能使与之相连的生色基最大吸收波长统统发生红移 ,而应具体问题具体分析 :对于n→π 来说 ,一方面助色基的p轨道和生色基的最低π 反键空轨道相互作用 ,使π 反键轨道能量上升 ,另一方面助色基的p轨道和生色基的n轨道正交 ,n轨道能量基本保持不变 ,因此n→π 跃迁能增加 ,吸收波长发生蓝移。对于π→π 跃迁来说 ,助色基的p轨道和生色基的最高π成键轨道相互作用生成的新的最高π成键轨道 ,能量虽然有所升高 ,但升高的程度与π 反键轨道升高的程度相比 ,在一些化合物中π轨道升高程度较大 ,因而π→π 跃迁能减小 ,吸收波长发生红移 ;在另一些化合物中π轨道升高程度较小 ,因而π→π 跃迁能增加 ,吸收波长发生蓝移。     

脉冲激光烧蚀推进技术的航天应用进展

脉冲激光烧蚀推进技术具有比冲高和推力可精确控制的特点,既可用于发射有效载荷也可用于星载动力,甚至可用小行星表面物质作为推进剂使其偏转轨道,因此,在航天领域得到越来越多关注。围绕激光单级入轨发射、同步轨道和火星轨道运输;激光微推力器用于航天器姿轨控,以及激光与电组合推进;激光烧蚀操控cm级空间碎片的轨道,以及激光烧蚀操控较大尺寸碎片的姿态;激光烧蚀偏转小行星轨道等方面,对脉冲激光烧蚀推进技术在航天领域研究现状和进展,进行了系统全面地归纳和总结,并对激光平均功率、波长、脉宽和推进剂选材等关键问题,进行了详细分析。     

基于MATLAB的HLS束流轨道慢反馈控制系统

束流轨道稳定性是同步辐射光源的重要性能指标, 直接影响实验线站光通量的稳定性. 介绍了在合肥光源储存环上实现束流轨道慢反馈校正的研究与实验工作, 目前合肥光源的全环垂直轨道的稳定性为Δy<±30μm, 从而使轨道的稳定性达到了国际同类机器先进水平.     

A new method for determination of satellite orbits by transfer

The original idea of a new method for determination of satellite orbits by transfer is from Two-Way Satellite Time and Frequency Transfer (TWSTFT). The original method is called “determination of satellite orbit by transfer”. The method is not only for determination of satellite orbit but also for the time transfer with high accuracy and precision. The advantage is that the accuracy and the precision for determination of satellite orbit are very high and the new method is favorable for various applications. The combination of various signals disseminated and received forms various modes of satellite orbit determinations. If receivers at stations receive the own station-disseminated signals via a satellite transponder, it forms an orbit determination mode called “receiving the own station-disseminated signals mode”. If receivers at all stations receive the signals disseminated from the master station via satellite transponders, it forms an orbit determination mode called “receiving the master station-disseminated signals mode”. If all of receivers at stations receive all stations-disseminated signals via satellite transponders, it forms an orbit determination mode called “receiving all stations-disseminated signals mode”. Also there are other combinations of signals for satellite orbit determination. For different orbit determination modes with different signal combinations, their rigorous formulae of processing are hereby presented in this paper. The accurate and the precise satellite orbit determination for both of the modes, “receiving the own station-disseminated signals mode” and “receiving the master station-disseminated signals mode” is attempted. It shows that the accuracy and precision for both of modes are nearly the same, the ranging accuracy is better than 1 cm, and the observation residuals of satellite orbit determination are better than 9 cm in the observation duration of 1 day. Supported by the National Basic Research and Development Program of China (Grant No. 2007CB815503100453001)     

环境温度对合肥光源束流轨道稳定性的影响

 环境温度是影响电子束流轨道稳定性的重要因素之一，国内外大多数加速器实验室为此都建立了较为完备的环境温度监测系统和恒温空调系统。合肥光源(HLS)是第二代光源，全环闭合轨道垂直方向上要求稳定在100 mm以内。为定量研究和分析环境温度对合肥光源的电子束流轨道的影响，建立了环境温度监测系统。着重介绍了环境温度监测系统的组成、辐射干扰问题以及数据分析方法。数据分析结果表明：环境温度与束流位置之间具有较强的相关性，垂直方向环境温度每变化1 ℃,束流位置变化10～20 mm。     

Chaos Behaviour of Molecular Orbit

Based on Hfickel＇s molecular orbit theory, the chaos and bifurcation behaviour of a molecular orbit modelled by a nonfinear dynamic system is studied. The relationship between molecular orbit and its energy level in the nonlinear dynamic system is obtained.     

Satellite-station time synchronization information based real-time orbit error monitoring and correction of navigation satellite in Beidou System

Satellite-station two-way time comparison is a typical design in Beidou System(BDS)which is significantly different from other satellite navigation systems.As a type of two-way time comparison method,BDS time synchronization is hardly influenced by satellite orbit error,atmosphere delay,tracking station coordinate error and measurement model error.Meanwhile,single-way time comparison can be realized through the method of Multi-satellite Precision Orbit Determination(MPOD)with pseudo-range and carrier phase of monitor receiver.It is proved in the constellation of 3GEO/2IGSO that the radial orbit error can be reflected in the difference between two-way time comparison and single-way time comparison,and that may lead to a substitute for orbit evaluation by SLR.In this article,the relation between orbit error and difference of two-way and single-way time comparison is illustrated based on the whole constellation of BDS.Considering the all-weather and real-time operation mode of two-way time comparison,the orbit error could be quantifiably monitored in a real-time mode through comparing two-way and single-way time synchronization.In addition,the orbit error can be predicted and corrected in a short time based on its periodic characteristic.It is described in the experiments of GEO and IGSO that the prediction accuracy of space signal can be obviously improved when the prediction orbit error is sent to the users through navigation message,and then the UERE including terminal error can be reduced from 0.1 m to 0.4 m while the average accuracy can be improved more than 27%.Though it is still hard to make accuracy improvement for Precision Orbit Determination(POD)and orbit prediction because of the confined tracking net and the difficulties in dynamic model optimization,in this paper,a practical method for orbit accuracy improvement is proposed based on two-way time comparison which can result in the reflection of orbit error.     

对角动量算符的讨论——对自旋的讨论之三

从算符^／J的构成上证明,所谓的总角动量J实质上是相对论性的轨道动量,自旋是相对论性轨道角动量的一个组成部分。