低轨卫星增强北斗三号导航星座性能分析

针对低轨卫星星座有待合理化设计的问题,深入研究了低轨卫星星座增强北斗三号系统定位性能。分析轨道高度、轨道倾角、星座构型对星座覆盖性能的影响,仿真北斗三号、GPS和3种不同类型的低轨星座,研究各低轨星座与北斗三号、GPS的组合系统在所选7个测站以及全球范围内的可见卫星数和PDOP值分布。结果表明低轨卫星对北斗三号的增强效果主要与低轨卫星数目有关,且不同轨道倾角的组合低轨星座有利于均衡系统在全球范围内的可见卫星数与PDOP值分布。低轨卫星有望通过改善卫星观测几何构型提高北斗三号系统的定位性能,且增强效果与低轨星座构型密切相关。     

GPS/LEO掩星技术中超折射效应的修正

在GPS掩星探测地球大气技术中，Abel积分变换要求大气折射指数n是折射半径a的单值函数，当大气折射率的垂直梯度达到小于一个极限值dN／dr≈-0．16N-unit m^-1上述单值性不成立，称其为超折射，此时Abel积分变换不再适用,如果还是在形式上应用经典的Abel变换，在反演结果中就会产生负大气折射率偏差．描述了低对流层中超折射现象的物理特性和数学表示；在广义Abel积分变换的基础上，讨论了超折射层内和超折射层下的大气剖面反演算法；选择了一个简单的采样间隔内等大气折射率垂直梯度假设，对英国高分辨率无线电探空观测资料进行模拟计算，验证了负超折射与大气折射率偏差的关系，并提出的广义Abel变换的合理性.     

Extraterrestrial samples from low Earth orbits: techniques for their collection and analysis

In the context of dust samples collections in space, the COMET experiment (Collecte en Orbite de Matière ExtraTerrestre) was proposed for the first time in 1982. The idea of such an experiment was to collect grains with identified cometary parent body, instead of mixing all extraterrestrial contributions present in low Earth orbit. It was thus proposed to install collectors inside hermetic boxes, to have these boxes mounted outside a space station, orbiting the Earth and to have the capability of choosing the time and duration of the collection. Since 1985, the COMET experiment has been exposed three times to space (COMET-1, in October 1985 during the encounter of the Earth with the Draconid meteor stream; the EUROMIR-95 instrument, exposing collectors, during the crossing by the Earth of the Orionid meteor stream associated to comet P/Halley and, in November 1998, during the crossing by the Earth of the Leonid meteor stream associated to comet Temple-Tuttle, COMET-99). Specific collection techniques, and corresponding analytical procedures have been developed. The collected particles are the only ones accessible in the laboratory with a known cometary origin, before the return to Earth (2006) of the Stardust mission, which will collect cometary grains in the tails of comet Wild 2. Such a challenge justifies the tremendous efforts brought into play, and that are summarized here.     

Position and velocity perturbations for the determination of geopotential from space geodetic measurements

Although space geodetic observing systems have been advanced recently to such a revolutionary level that low Earth Orbiting (LEO) satellites can now be tracked almost continuously and at the unprecedented high accuracy, none of the three basic methods for mapping the Earth’s gravity field, namely, Kaula linear perturbation, the numerical integration method and the orbit energy-based method, could meet the demand of these challenging data. Some theoretical effort has been made in order to establish comparable mathematical modellings for these measurements, notably by Mayer-Gürr et al. (J Geod 78:462–480, 2005). Although the numerical integration method has been routinely used to produce models of the Earth’s gravity field, for example, from recent satellite gravity missions CHAMP and GRACE, the modelling error of the method increases with the increase of the length of an arc. In order to best exploit the almost continuity and unprecedented high accuracy provided by modern space observing technology for the determination of the Earth’s gravity field, we propose using measured orbits as approximate values and derive the corresponding coordinate and velocity perturbations. The perturbations derived are quasi-linear, linear and of second-order approximation. Unlike conventional perturbation techniques which are only valid in the vicinity of reference mean values, our coordinate and velocity perturbations are mathematically valid uniformly through a whole orbital arc of any length. In particular, the derived coordinate and velocity perturbations are free of singularity due to the critical inclination and resonance inherent in the solution of artificial satellite motion by using various types of orbital elements. We then transform the coordinate and velocity perturbations into those of the six Keplerian orbital elements. For completeness, we also briefly outline how to use the derived coordinate and velocity perturbations to establish observation equations of space geodetic measurements for the determination of geopotential.     

一种基于LEO卫星信标的电离层层析成像新算法

LEO卫星信标是电离层监测的重要手段之一.利用电离层层析成像算法,LEO卫星信标能够实现区域电离层电子密度的快速重构.针对LEO卫星信标的特点,本文提出了一种函数基模型与像素基模型组合的电离层层析成像新算法.选择差分相对电离层总电子含量作为输入数据源,先通过函数基模型法获取电离层电子密度初始分布,再利用像素基模型法对初始分布进行二次迭代重构,该方法可有效降低电离层层析成像对背景电离层模型的依赖,同时能够实现电离层小尺度扰动结构的有效反演.利用数值仿真方法及低纬度电离层层析成像网的实测数据的反演结果验证了本文提出的新算法的可行性和可靠性.     

大气阻力引起卫星轨道衰减的数值模拟

本文以德国低轨道卫星CHAMP为例,联合考虑地球扁率和大气阻力摄动的影响,对相应摄动方程进行数值积分,计算轨道根数变化,并进而计算得到卫星空间位置,由此模拟考察大气阻力引起的轨道高度衰减.模拟中使用综合考虑了太阳辐射和磁暴等多种因素影响的最新国际大气标准JB2008模式来计算热层大气密度. 选取CHAMP卫星轨道高度自然衰减（无点火提升卫星高度操作）的2005全年进行模拟;为了考察不同年份阻力系数的可能变化,对2002年1—3月处在较大高度的轨道也进行了模拟.考虑到CHAMP卫星的特殊几何构形及飞行高度的热层温度条件,取阻力系数大于2.8,并在一定范围内变化,以求得模拟与实际轨道衰减符合较好.结果表明,对于2005年,阻力系数为2.91时模拟得到的轨道高度的衰减与实际轨道衰减符合得最好,模拟与实际轨道半长轴全年的标准偏差为81m;在卫星高度稍高的2002年,模拟的最佳阻力系数为3.0;模拟所得最佳阻力系数值比传统使用的值2.2大30%以上.由于在模拟中忽略了高阶保守力分量,所得近/远地点高度没有出现实际轨道所显示的周期性起伏.     

GPS无线电掩星监测地球大气技术中的一种长时间序列地面测点方法

ＧＰＳ无线电掩星技术是从行星无线电遥感探测技术发展而来。从８０年代末以来,这种技术在气象学的应用研究中获得新的发展,自从第一颗实验低轨地球卫星（ＬＥＯ卫星）ＭｉｃｏＬａｂｌ在１９９５年４月３日发射升空以后,它所获得的数据和成果已经证实了ＧＰＳ无线电掩星技术在地球大气分层结构的探测上所具有潜在科学价值。但是,延长地面测点的时间覆盖无疑对这种技术在气象和大气的研究上有很大的好处,因而提出一种用低轨通约     

GPS掩星切点水平漂移规律的数值研究

在现有GPS星座和大气球对称假设条件下，利用射线追踪法对掩星事件进行了数值模拟，讨论了大气折射指数垂直分布、LEO卫星轨道倾角和高度对GPS掩星切点水平漂移的影响情况。结果表明:在太阳活动剧烈的白天和夜间两种典型情况下，切点平均水平漂移变化约20 km；对735 km高度的LEO卫星来说，轨道倾角在130°附近时，切点平均水平漂移最小，并随着倾角向0°或180°变化，切点平均水平漂移均增大，但在55°附近时随倾角变化稍有波动；对倾角为70°的LEO卫星来说，当轨道高度从400 km变化到1500 km时，切点平均水平漂移变化约141 km，且随高度增加而单调减小     

区域监测站与低轨卫星数据联合测定MEO卫星轨道

我国北斗二代系统(BDS)地面运控监测站数量较少且为区域分布,短期内难以实现全球建站,因此对全球运行的中圆地球轨道卫星(MEO)难以形成连续多重覆盖观测,导致BDS的MEO实时轨道精度偏低。基于上述问题,本文考虑到低轨卫星星载GNSS数据可以有效弥补区域监测站在空间覆盖及几何结构上的不足,设计了一种将星载GNSS接收机作为高动态天基监测站,联合地面区域监测站数据对卫星导航系统的MEO卫星轨道进行实时解算预报的方法。算例结果显示:7个区域监测站联合1至3个天基监测站,其定轨精度可分别提升约21%、34%和55%,这也表明,地面区域监测站联合天基低轨卫星数据可有效提高MEO卫星的轨道精度。建议我国BDS在区域测站分布阶段可采用联合低轨卫星数据方法提高北斗MEO卫星实时轨道精度。     

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