话说天球

仰望天空,我们感到自己仿佛处身一个硕大半球的中心,而地平面延伸过去就是天与地的界线。无论是太阳、月亮,还是繁星,好像都镶嵌在这个半球球面上。每天,太阳东升西落,在这个半球上划过一道圆弧     

基于CAPS,BDS和GPS的组合卫星定位精度分析

随着GPS,GLONASS,Galileo和BDS等全球卫星定位系统的建设和完善,同时采用两个或两个以上定位系统信号进行多系统组合定位成为导航领域研究的热点。相比传统的单系统定位,多系统组合具有更好的定位、测速、授时性能以及更强的环境适应性。通过CAPS,BDS和GPS三个系统的静态单点联合定位解算,实现了转发式定位系统与直发式定位系统的联合定位,验证了中国区域定位系统参与多系统全球导航卫星系统定位的可行性,并分析了组合定位的性能与定位精度。分析表明,中国区域定位系统参与多系统联合定位解算是完全可行的,单点定位精度优于3 m,且还有提高的空间。中国区域定位系统的加入,丰富了全球导航卫星系统的选择,对提高全球导航卫星系统联合定位的多样性,改善联合定位性能具有研究意义及应用价值。     

木星伽利略卫星的“相互掩食”现象

木星绕太阳公转一圈约12年,每隔6年则过春分或秋分点一次。在此前后,对木星而言,太阳带着地球通过其赤道平面。也就是说,木星、运行轨道与木星赤道夹角小于0.5度的四颗伽利略卫星、地球以及太阳几乎在同一个平面,结果是伽利略卫星产生互相遮掩或将自己的阴影投射在另一颗卫星上的现象能被地球上     

广义延拓法在GPS精密星历内插和外推中的应用

利用精密星历解算卫星坐标是实现全球定位系统高精度差分定位的首要基础,受限于全球定位系统精密星历的采样时间间隔,为了得到任意时刻的卫星坐标,需要对全球定位系统精密星历数据做内插和外推处理。分析卫星位置随时间变化的规律后,采用广义延拓法对卫星的一段轨道构造以时间为坐标的内插和外推模型,在不引入较大位置误差的同时简化了卫星坐标的计算过程,并与拉格朗日插值法进行对比实验。研究结果表明,利用广义延拓法内插时误差小于5 cm,且在外推30 min内仍然能维持精度,明显优于拉格朗日插值法。     

低轨通信卫星多普勒定位性能分析

为了研究低轨通信卫星多普勒定位性能,首先分析了低轨卫星的对地覆盖特性、信号传输特性以及多普勒频移特性,推导了多普勒定位原理和方法,提出了适用于多普勒定位的精度因子.基于已在轨的铱星和全球星系统,解算了全球范围可见卫星数和定位精度因子,并对相应测站进行了定位仿真实验和误差分析.结果表明:对于铱星和全球星系统,随着纬度降低,卫星可见数减小,多普勒几何精度因子变大;多普勒定位结果精度同时受到频率测量精度、卫星位置误差以及卫星速度误差影响,当卫星位置误差小于10 m、卫星速度误差小于0.1 km·s^-1时,对定位结果影响不大,此时频率测量精度成为影响定位精度的决定性因素,且当频率测量精度为0.01 Hz时,定位精度可达1.18 m.     

球面反射镜各圆带区焦点位置和轴上球差

球面反射镜各圆带区焦点位置和轴上球差张国新球面可看成圆绕直径旋转而形成的。因而，球面的光学性质可通过讨论相应圆的光学性质而知道。设与球面相应的圆的方程为ｘ２＋ｙ２＝Ｒ２，当ｙ＝ｂ时，这里只讨论ｂ≥０、ｘ≥０的情况就可以了。图一中，Ａ表示回上的点（人死...     

一种小视场照象天体定位方法的理论基础

本文利用了小视场照象象场畸变小的长处,解出可应用于小视场的天球球面坐标与底片理想坐标的简化关系式ξ=(α-A)·cosδ,η=δ-D。研究了小视场底片上天体的相互关系的变化,并讨论了怎样将众多小视场图象联结成包含有标准星、特测星的大视场天区的可能性,从数学上“微分”的概念出发,给出一种近似定位方法的理论计算证明。这种方法特别适用于新兴的光电器件(如电荷耦合器件CCD),可以充分发挥其量子效率高的长处,又解决了应用于照象天体测量的视场过小的缺点,能仅仅使用这类装置快速、准确地测定待测天体的位置。尤其对暗天体的定位可以显出这一方法的长处。     

转动恒星结构与演化研究

恒星的自转 ,是恒星结构和演化理论的难点。近年来有许多观测事实 ,特别是早型大质量星的观测事实 ,预示恒星的自转效应可能引起恒星内部的物质向外转移 ,造成恒星表面一些元素丰度超丰 ,并且对恒星结构和演化产生重要影响 ,因此 ,恒星的自转问题受到了越来越多的关注。考虑自转效应后 ,恒星结构和演化模型将是二维模型 ,本文综述了诸多作者如何将二维的恒星结构和演化模型简化为一维模型。作者在研究了以上作者的简化方法后 ,提出了一种比较简单的新方法。这种方法基于如下假设 :假设在等势面上的温度 ,密度 ,压强 ,光度 ,化学组成和角速度等物理和化学量近似于均匀分布 ,并且这些量与等价球面上的量相同。 (等价球面是假想的球面 ,它包围的体积与等势面包围的体积相等。)我们在等价球面上推出新的转动恒星结构和演化方程 ,构造出新的演化模型。这个模型与不考虑转动效应的演化模型相比 ,有以下变化 :流体静力学平衡方程变化 ;辐射温度梯度变化 ,并引起对流判据变化 ;星风物质损失和角动量损失增大。作为转动恒星结构和演化模型的应用 ,我们研究了中 ,小质量星中心氦燃烧阶段在赫罗图中的演化轨迹发生来回摆动 (又称为蓝回绕 )的物理机制问题。有诸多作者曾经研究了可以影响蓝回绕的各种因素。但是不知     

Walker星座PDOP分析

分析多种walker星座的PDOP,研究walker星座的轨道构型参数:轨道高度、轨道倾角、平面数、卫星颗数、调相因子对导航可用性的影响.并得出在平面数为3时,只需24颗卫星即可达到全球PDOP值小于3,这也是实现全球PDOP值小于3的Walker星座中所需卫星颗数最小的星座.     

北斗卫星导航系统服务精度评估

精度是北斗卫星导航系统(Beidou Navigation Satellite System,BDS)服务指标体系的重要内容.给出了北斗卫星导航系统精度指标的含义及精度指标的评估方法,利用实测数据分析了北斗系统实际实现的精度指标,并将其与GPS系统实际实现的精度指标作比较分析.DOP(几何精度因子)值由卫星导航系统空间星座分布决定,是影响用户定位授时精度的重要因素,比较了北斗与GPS在中国区域DOP值分布的差异.GPS系统PDOP(定位几何精度因子)分布均匀,随用户经度和纬度变化不大,在1.0–2.0之间.而受混合星座影响,北斗系统PDOP分布随着测站经度和纬度变化较大,变化范围为1.5–5.0;且随测站纬度增加而变大,由中心经度(东经118?)向两侧不断变大.对于影响用户等效距离误差的空间信号精度进行了比较分析.利用IGS(国际GNSS服务组织)提供的事后精密轨道、激光跟踪数据和北斗双向时频传递测量的卫星钟差评估了北斗基本导航电文的精度.结果表明:北斗IGSO(倾斜地球同步轨道)卫星和MEO(中轨道)卫星轨道径向误差约为0.5 m,大于GPS卫星轨道小于0.2 m的径向误差.北斗GEO(地球同步轨道)卫星激光残差约为65 cm,IGSO卫星和MEO卫星激光残差约为50 cm.受卫星钟差数据龄期影响,MEO卫星钟差参数误差明显大于IGSO卫星和GEO卫星,约为0.80 m.最后,采用MGEX(多GNSS系统试验项目)多模接收机进行了定位试验,分析了北斗系统和GPS在定位精度上的差异.结果表明:受星座构型影响,北斗卫星导航系统定位精度与GPS系统定位精度相比有所差异,但满足水平定位精度优于10 m、高程定位精度优于10 m的设计要求,双系统组合定位精度好于单一系统定位精度.     

Motion of the orbital plane of a satellite due to a secular change of the obliquity of its mother planet

At the present state the rotational axes of Uranus and Pluto are nearly perpendicular to their orbital planes and each satellite moves in the vicinity of the equatorial plane of its mother planet. We assume that in the past a planet's equatorial plane was nearly coincident with its orbital plane and then the inclination of the equatorial plane with respect to the orbital plane began to increase secularly. Here we discuss whether a satellite that moves in its mother's equatorial plane continues to move in the equatorial plane or not. When the direct solar perturbation is neglected, the satellite continues to stay in the equatorial plane under the condition that the secular rate of change of the obliquity is slower than the precessional speed of the satellite orbital plane with respect to the equator.     

An Improved Grey Model and Its Application Research on the Prediction of Real-time GPS Satellite Clock Errors

In the work on the real-time GPS precise point positioning, the realtime and reliable prediction of the satellite clock error is one of the keys to the realization of the GPS real-time high accuracy point positioning. The satelliteborne GPS atomic clock has high frequency, is very sensitive and extremely easy to be influenced by the outside world and its own factors. Therefore, it is very difficult for one to know well its complicated and detailed law of change, with these attributes being in accordance with the characteristics of the theory of grey system. Thus, it is considered that the process of variation of the clock error is regarded as a grey system. On the basis of the exploration of the limitations of the quadratic polynomial and grey model satellite clock error predictions, the research on the real-time prediction of the GPS satellite clock error by taking advantage of the improved grey model is proposed. Finally, the materials of the GPS satellite clock error of 3 different time intervals are used to make the accuracy analysis of the clock error prediction of different sampling intervals, to study the relation between the grey model exponential coefficient and the prediction accuracy and to make the analysis of the comparison of the prediction accuracy with that of the quadratic polynomial method. The general relation between the different types of satellite clock errors and the model exponential coefficients is summarized and compared with the IGS final clock error ephemeris product to test and verify the feasibility and availability of the improved prediction model proposed in the present article so as to provide the higher-accuracy satellite clock error products for the real-time GPS dynamic precise point positioning.     

The radiation environment in a low earth orbit:the case of BeppoSAX

Low-inclination, low altitude Earth orbits (LEO) are of increasing importance for astrophysical satellites, due to their low background environment. Here, the South Atlantic Anomaly (SAA) is the region with the highest amount of radiation. We study the radiation environment in a LEO (500–600 km altitude, 4^° inclination) through the particle background measured by the Particle Monitor (PM) experiment onboard the BeppoSAX satellite, between 1996 and 2002. Using time series of particle count rates measured by PM we construct intensity maps and derive SAA passage times and fluences. The low-latitude SAA regions are found to have an intensity strongly decreasing with altitude and dependent on the magnetic rigidity. The SAA extent, westward drift and strength vs altitude is shown.     

基于SLR精密轨道的天文定位精度分析

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.     

BDS-3新频点信号双频精密单点定位精度分析

北斗卫星导航系统(BeiDou navigation satellite System, BDS)已于2020年7月正式建成并开通, 北斗三号(BDS-3)在旧信号B1I和B3I的基础上, 增加了B1C、B2a新信号. 为了全面评估BDS-3的新信号B1C、B2a的定位性能, 试验了GPS (Global Positioning System)、BDS-3、BDS-2/BDS-3新旧信号的定位性能和BDS系统不同频点与GPS组合定位性能, 对BDS (B1I+B3I、B1C/B2a)+GPS (L1+L2)组合静态PPP (Precise Point Positioning)定位性能进行分析, 并与单卫星系统对比分析. 试验结果表明: BDS-3 (B1C/B2a)在East (E)、\lk North (N)、Up (U)方向的定位精度优于1.25cm、0.89cm、1.67cm, BDS-3新旧频点在E、N方向上定位精度与GPS L1/L2在同一水平上, U方向上新频点定位精度高于GPS L1/L2和BDS-3旧频点, 较旧频点定位精度提升了34.2%, 新频点收敛时间25.9min比旧频点提升了12.7%; 相较于BDS、GPS单系统, 组合系统BDS/GPS定位精度和收敛时间有了明显的提高, BDS-3 (B1C/B2a)+GPS在E、N方向上与BDS-3 (B1I/B3I)+GPS定位精度相当, 在U方向上定位精度前者较后者有了明显的提升, 提升了17.2%, 组合系统新频点收敛时间20.1min比旧频点提升了17.6%.     

The geometry of impacts on a synchronous planetary satellite

We consider a satellite in a circular orbit about a planet that, in turn, is in a circular orbit about the Sun; we further assume that the plane of the planetocentric orbit of the satellite is the same as that of the heliocentric orbit of the planet. The pair planet–satellite is encountered by a population of small bodies on planet-crossing, inclined orbits. With this setup, and using the extension of Öpik’s theory by Valsecchi et al. (Astron Astrophys 408:1179–1196, 2003), we analytically compute the velocity, the elongation from the apex and the impact point coordinates of the bodies impacting the satellite, as simple functions of the heliocentric orbital elements of the impactor and of the longitude of the satellite at impact. The relationships so derived are of interest for satellites in synchronous rotation, since they can shed light on the degree of apex–antapex cratering asymmetry that some of these satellites show. We test these relationships on two different subsets of the known population of Near Earth Asteroids.     

第三代卫星导航定位系统星载原子钟的新发展

传统铷原子钟和铯原子钟已在卫星导航定位系统中作为星载原子钟获得重要应用.卫星导航定位系统的更新和新发展要求更高精度更小型的新型星载原子钟.该文介绍采用新物理原理和先进技术在下-代卫星导航定位系统有应用前景的新原子钟的产生和发展以及它们目前的进展.     

Effects of motion of the equatorial plane on the orbital elements of an earth satellite

Exact differential equations relating the perturbations to satellite orbital elements by the motion of the Earth's equatorial plane are derived, and they are solved to second order in precession. The system proposed in a previous paper (Kozai, 1960), in which the inclination and the argument of perigee are referred to the equator of date and the longitude of the ascending node is measured from a fixed point along a fixed plane and then along the equator of date, can still be recommended for precise studies of satellite motion even when the second-order perturbations are taken into account.     

The general equilibria of a spinning satellite in a circular orbit

Let a rigid satellite move in a circular orbit about a spherically symmetric central body, taking into account only the main term of the gravitational torque. We shall investigate and find all solutions of the following problem: Let the satellite be permitted to spin about an axis that is fixed in the orbit frame; the satellite need not be symmetric, the spin not uniform, and the spin axis not a principal axis of inertia. The complete discussion of this type of spin reveals that the cases found by Lagrange and by Pringle - and the well-known spin about a principal axis of inertia orthogonal to the orbit plane — are essentially the only ones possible; the only further (degenerate) case is uniform spin of a two-dimensional, not necessarily symmetric satellite about certain axes that are orthogonal to the plane containing the body and to the orbit of the satellite around the central body.