由CHAMP星载GPS相位双差数据解算地球引力场模型

利用7d的CHAMP星载GPS相位观测数据和48个IGS跟踪站的观测数据，构造星地双差相位观测量，进行GPS数据预处理；利用Cowell Ⅱ数值法进行轨道积分和分块Bayes最小二乘参数估计，解算了地球引力场位系数。该模型与EGM96相比（70阶次），大地水准面起伏差异最大为2．872m，差弄精度为0．522m，平均差异为-0．003m，这说明本文解算的地球重力场模型与EGM96没有系统性差异。     

星载GPS观测数据预处理模型研究

星载GPS不同于地基GPS。为了进行基于星载GPS的低轨卫星精密定轨和地球重力场模型解算,本文研究了星载GPS观测数据的钟差改正、整周模糊度解算、周跳探测、卫星跟踪点改正、GPS天线相位中心偏移和改正等的模型,给出了对应的处理公式和处理过程。     

由星载GPS双差相位数据进行CHAMP卫星动力学定轨

为了确定CHAMP卫星的轨道，由星载GPS数据和IGS跟踪站的GPS数据构造星地相位双差观测量，利用EOP、SGO、时间等数据，对GPS数据进行预处理，包括钟差改正、模糊度解算和周跳探测、卫星姿态改正、天线偏差和相位中心改正等，采用CHAMP卫星受力摄动模型，根据动力学原理，对CHAMP卫星进行实际定轨。与德国GFZ定轨结果PSO相比，本方法定轨结果径向精度为0．2857m。对于1d的重叠轨道，径向轨道差异的RMS为0．0958m。对于轨道端点比较，径向轨道差异平均为0．0666m。     

长距离GPS/BDS参考站网多频载波相位整周模糊度解算方法

长距离网络RTK是实现GPS/BDS高精度实时定位的主要手段之一,其核心是长距离参考站网GPS/BDS整周模糊度的快速准确确定。本文提出了一种长距离GPS/BDS参考站网载波相位整周模糊度解算方法,首先利用GPS双频观测数据计算和确定宽巷整周模糊度,同时利用BDS的B2、B3频率观测值确定超宽巷整周模糊度。然后建立GPS载波相位整周模糊度和大气延迟误差的参数估计模型,附加双差宽巷整周模糊度的约束,解算双差载波相位整周模糊度,并建立参考站网大气延迟误差的空间相关模型。根据B2、B3频率的超宽巷整周模糊度建立包含大气误差参数的载波相位整周模糊度解算模型,利用大气延迟误差空间相关模型约束BDS双差载波相位整周模糊度的解算。克服了传统的使用无电离层组合值解算整周模糊度的不利影响。采用实测长距离CORS网GPS、BDS多频观测数据进行算法验证,试验结果证明该方法可实现长距离参考站网GPS/BDS载波相位整周模糊度的准确固定。     

星载GPS载波相位测量的周跳探测方法研究

提出了一种基于粗差探测理论的星载GPS载波相位数据周跳的探测方法。并编制了相关软件对CHAMP星载GPS测量数据进行了验算。结果表明，当跟踪的有效GPS卫星多于5颗时。能够探测出所有的周跳。     

GAAF在星载GPS实时定轨中的应用研究

为确保高精度星载GPS实时定轨算法能够应用于较低轨道卫星,提出了用地球引力近似函数法(GAAF)代替传统球谐函数递推法来计算地球引力加速度,在不降低实时定轨精度的同时,大幅减小高阶次重力场模型的轨道积分计算负荷,以满足计算能力有限的星载处理器的在轨处理要求。分析了影响GAAF计算精度的两个因素:伪中心位置拟合多项式的次数选取和经纬度格网大小的最优确定。用CHAMP卫星的实测GPS数据模拟实时定轨试验,结果表明,采用二次及以上伪中心拟合多项式,格网纬度小于0.75°、经度小于1.5°的GAAF时,实时定轨的轨道精度要优于70×70阶次重力场模型直接参与实时定轨,且大幅降低实时定轨的计算负荷。     

基于小波变换的单频GPS快速精密定位整周模糊度的解算

对于GPS短基线,载波相位双差观测量已基本消除了卫星轨道误差、钟差、大气折射误差等系统偏差的影响,主要包含距离观测量信息及随机测量误差,其中测量误差是高频的测量噪声,小波变换可将GPS载波相位双差观测量中的观测噪声(高频部分)分解出来。本文利用Coiflets小波基函数对GPS快速定位的原始载波相位双差观测量进行5层分解,通过重构第5层低频系数获得去除噪声的"干净"的载波相位双差观测量,然后利用"干净"的双差观测量进行最小二乘参数估计,以减小测量噪声对GPS快速定位病态方程解的扰动。计算结果表明该方法能够显著提高GPS快速定位中模糊度浮点解的精度,仅利用几个观测历元的数据就可以准确地固定模糊度。     

卫星重力与地球重力场

卫星重力探测技术可获取全球均匀覆盖的地球重力场信号。以GRACE为代表的卫星跟踪卫星（satellite—to—satellite tracking,SST）计划为人类提供了前所未有丰富的中长波尺度的全球地球重力场信息。本文包含两部分研究内容：一是给出基于能量守恒原理的GRACESST重力观测方程,并采用此方法以实测GRACE观测数据求解得到120阶的GRACE地球重力场模型WHU—GM—05,并同国际上具有代表性的类似模型进行了分析比较;二是采用解析方法分析了SST观测系统中KBR、ACC、星载GPS等有效栽荷误差与获取地球重力场信号性能的响应,为我国SST设计和实施提供参考。     

LEO星载GPS双向滤波定轨研究

介绍了目前常用的LEO(low Earth orbiter)星载GPS定轨方法,分析了LEO星载GPS双向滤波定轨方法与其他几种主要定轨方法的区别.从卫星运动方程和星载GPS非差定轨观测方程出发,给出了LEO星载GPS双向滤波定轨方法的原理,采用自行研制的定轨软件对两颗GRACE(gravity recovery and climate ex-periment)卫星进行了定轨试验,通过与JPL(Jet Propulsion Laboratory)轨道的对比及KBR(k-band rangingsystem)观测数据的外部检核发现:①双向滤波定轨技术不仅能显著提高单向滤波开始阶段的定轨精度,而且可以从整体上提高卫星的定轨精度;②LEO星载GPS双向滤波定轨方法切实可行,相应的星载GPS定轨软件对GRACE卫星定轨精度在径向、沿轨方向和法向优于5 cm.     

地球重力场模型在平面控制网中的应用

现在精密工程测量中GPS与全站仪的共用是普遍存在的事实,这必然存在法线系统与垂线系统的转换问题,以往由于重力场模型精度较低,未能充分顾及到这种差别,而利用现有最新的地球重力场模型,能较精确地计算垂线偏差并将其应用于精密工程测量。本文提出了顾及垂线偏差的GPS与全站仪的精密数据处理方法,通过"三差改正"将全站仪观测值转化为法线系统下的观测值,与GPS数据统一处理,利用某隧道算例验证了地球重力场模型对平面控制网数据处理的影响不容忽视。     

Swarm卫星星载GPS精密定轨方法及精度分析

Swarm星座是ESA的首个用于测量来自地球核心、地幔、地壳、海洋、电离层等区域磁场信息的对地观测卫星星座。而高精度的轨道信息正是其有效利用卫星载荷完成上述任务的前提条件。目前国内关于Swarm卫星精密定轨的研究较少,为此建立并推导了Swarm卫星精密定轨的动力学模型、观测模型以及它们之间的数学关系,详细给出了Swarm卫星精密定轨模型与实现过程。针对Swarm卫星精密定轨中姿态数据的处理问题提出了相应的解决方案。利用Swarm卫星星载GPS实测数据,采用约化动力学定轨方法进行Swarm卫星精密定轨实验。通过轨道衔接点位置差异、与外部精密轨道比较以及SLR验证等精度评定方法分析表明:基于星载GPS的Swarm卫星约化动力学定轨各方向的精度都优于3 cm。     

地球重力场、重力、重力梯度在三维直角坐标系中的表达式

现代卫星重力测量主要利用星载GPS接收机、加速度计、星载测距仪等来确定重力卫星的轨道 ,削弱非保守力的干扰 ,由此根据卫星的位置、速度及其变率来确定地球重力场。而上述GPS等星载仪器所提供的数据 ,包括卫星轨道坐标及其速率、扰动加速度、星间距离及其变率 ,都是以三维直角坐标 (x ,y ,z)的形式表示的 ,因此 ,地球重力场、重力和重力梯度在三维直角坐标系中的表达式在卫星重力解算中具有实际意义     

Precise orbit determination for the GRACE mission using only GPS data

The GRACE (gravity recovery and climate experiment) satellites, launched in March 2002, are each equipped with a BlackJack GPS onboard receiver for precise orbit determination and gravity field recovery. Since launch, there have been significant improvements in the background force models used for satellite orbit determination, most notably the model for the geopotential. This has resulted in significant improvements to orbit accuracy for very low altitude satellites. The purpose of this paper is to investigate how well the orbits of the GRACE satellites (about 470 km in altitude) can currently be determined using only GPS data and based on the current models and methods. The orbit accuracy is assessed using a number of tests, which include analysis of orbit fits, orbit overlaps, orbit connecting points, satellite Laser ranging residuals and K-band ranging (KBR) residuals. We show that 1-cm radial orbit accuracy for the GRACE satellites has probably been achieved. These precise GRACE orbits can be used for such purposes as improving gravity recovery from the GRACE KBR data and for atmospheric profiling, and they demonstrate the quality of the background force models being used.     

基于宽巷/窄巷法的星载GPS相位数据的模糊度解算和周跳探测

星载GPS技术是卫星精密定轨及其任务顺利执行的关键,而模糊度和周跳问题是星载GPS相位数据应用的难题。本文利用宽巷/窄巷法对星载GPS相位数据进行模糊度计算和周跳探测,给出了模糊度计算和周跳探测的计算公式和解算步骤。利用宽巷/窄巷法对CHAMP卫星实际星载GPS数据进行了处理,结果表明该方法是可行的,同时由于卫星的高速运动,星载GPS数据的模糊度解算和周跳探测难度也较大。     

Precise relative orbit determination of twin GRACE satellites

When formation flying spacecrafts are used as platform to gain earth oriented observation, precise baselines between these spacecrafts are always essential. Gravity recovery and climate experiment (GRACE) mission is aimed at mapping the global gravity field and its variation. Accurate baseline of GRACE satellites is necessary for the gravity field modeling. The determination of kinematic and reduced dynamic relative orbits of twin satellites has been studied in this paper, and an accuracy of 2 mm for dynamic relative orbits and 5 mm for kinematic ones can be obtained, whereby most of the double difference onboard GPS ambiguities are resolved.     

激光在天空对地观测中的应用

1960年7月世界上第一台激光器问世后，激光测距迅速兴起，不管是地面激光测距，还是激光测卫和激光测月，都为大地测量学的发展作出了重大贡献；特别是激光测卫测月成果，为我们深化对地球动态效应的认识，揭示地球的奥秘，提供了许多重要的科学数据，本文综析了值得注视的下列新近发展。.在IGEX-98国际大联测中，求定GLONASS卫星的激光轨道与微波轨道之差；.评定PRN05/06号GPS卫星星历的精度；.检核Topex/Poseidon海洋测高卫星用GPS定轨的测量误差，.用机载激光测深系统测量海水的浓度；.用EOS-ALT星载激光测距/测高系统测量地球动态参数。     

Precise orbit determination of the Fengyun-3C satellite using onboard GPS and BDS observations

The GNSS Occultation Sounder instrument onboard the Chinese meteorological satellite Fengyun-3C (FY-3C) tracks both GPS and BDS signals for orbit determination. One month’s worth of the onboard dual-frequency GPS and BDS data during March 2015 from the FY-3C satellite is analyzed in this study. The onboard BDS and GPS measurement quality is evaluated in terms of data quantity as well as code multipath error. Severe multipath errors for BDS code ranges are observed especially for high elevations for BDS medium earth orbit satellites (MEOs). The code multipath errors are estimated as piecewise linear model in \(2{^{\circ }}\times 2{^{\circ }}\) grid and applied in precise orbit determination (POD) calculations. POD of FY-3C is firstly performed with GPS data, which shows orbit consistency of approximate 2.7 cm in 3D RMS (root mean square) by overlap comparisons; the estimated orbits are then used as reference orbits for evaluating the orbit precision of GPS and BDS combined POD as well as BDS-based POD. It is indicated that inclusion of BDS geosynchronous orbit satellites (GEOs) could degrade POD precision seriously. The precisions of orbit estimates by combined POD and BDS-based POD are 3.4 and 30.1 cm in 3D RMS when GEOs are involved, respectively. However, if BDS GEOs are excluded, the combined POD can reach similar precision with respect to GPS POD, showing orbit differences about 0.8 cm, while the orbit precision of BDS-based POD can be improved to 8.4 cm. These results indicate that the POD performance with onboard BDS data alone can reach precision better than 10 cm with only five BDS inclined geosynchronous satellite orbit satellites and three MEOs. As the GNOS receiver can only track six BDS satellites for orbit positioning at its maximum channel, it can be expected that the performance of POD with onboard BDS data can be further improved if more observations are generated without such restrictions.     

An Alternative Orbit Integration Algorithm for GPS-Based Precise LEO Autonomous Navigation

Single-epoch point positioning with the global positioning system (GPS) is as accurate in low orbit as it is on the ground: typically a three-dimensional rms accuracy of 20 to 30 m as the selective availability turns to zero. This is achieved at any observation epoch without orbit dynamic information. With sophisticated models and filtering techniques onboard the spacecraft, the orbit accuracy of a Low Earth Orbiter (LEO) can be improved to a few meters using the civilian broadcast GPS signals. To achieve this accuracy autonomously in real time, an efficient onboard computing processor is required to carry out the sophisticated orbit integration and filtering process. In this paper, a new orbit integrator is presented that computes the nominal orbit states (the position and velocity) and the state transition equations with numerical methods of integral equation, instead of differential equation usually used for orbit computation. The algorithm is simple, and can be easily embedded in an onboard processor. The numerical results demonstrate that the proposed method of the integral equation provides precise orbit predictions over several orbits. The sequential filter based on the above integrator allows the use of simple orbit state equations to efficiently correct dynamical model errors with precise GPS measurements or improve the orbits using GPS navigaion solutions from the 3D rms accuracy of 26 m to 3.7 m within a few hours of tracking. ? 2001 John Wiley & Sons, Inc.