一种基于IGS超快星历的区域性实时精密单点定位方法

实时GPS精密单点定位需要实时的卫星轨道和钟差产品,为此提出一种利用区域GPS连续运行参考站和IGS发布的IGU超快轨道进行实时精密单点定位的方法.该方法首先利用连续运行参考站观测数据与IGU超快轨道预报部分进行实时GPS卫星钟差的估计,然后利用估计得到的实时GPS卫星钟差产品和IGU超快轨道预报部分,进行用户GPS接...     

利用星载GPS数据确定厘米级Jason-1卫星精密轨道

利用Jason-1卫星星载GPS实测数据,通过非差简化动力学定轨的方法,计算Jason-1卫星2003年1月3日至23日的轨道,并与JPL确定的GPS简化动力学轨道进行对比。结果表明,简化动力法使Jason-1卫星的径向定轨精度可优于±2.5 cm。     

利用GPS伪距观测值确定低轨卫星轨道的探讨

介绍了通过建立卫星的轨道动力学模型,设计出GPS观测方程和运动方程组合的卡尔曼滤波模型。探讨了使用卡尔曼滤波对所得轨道进行滤波平滑,指出了影响精度的因素和提高精度的办法。     

JASON-3卫星星载GPS厘米级精密定轨

针对JASON-3卫星精密定轨方法和轨道精度检核的关键问题,该文利用4d的星载GPS观测数据,基于简化动力学定轨方法实现JASON-3精密定轨,并提出采用内部符合和外部符合两种方法对解算轨道进行检核。通过重叠轨道对比,径向、切向和法向轨道精度均在0.5cm左右;将解算的简化动力学轨道与DORIS国际服务组织(IDS)的多任务精密卫星测高、卫星定轨和定位地面部分提供的SSA精密轨道进行对比,4d的轨道精度在径向、切向和法向分别达1.57～2.18cm、2.22～3.55cm和2.60～2.89cm。实验结果表明,JASON-3测高卫星的简化动力学轨道精度达厘米级,满足该卫星对轨道精度的要求。     

SWARM卫星简化动力学厘米级精密定轨

联合星载GPS双频观测值与简化的动力学模型,在卫星运动方程中引入适当的伪随机脉冲参数,对SWARM卫星进行精密定轨。采用星载GPS相位观测值残差、重叠轨道以及与外部轨道对比等3种方法对SWARM卫星简化动力学定轨结果进行检核。结果表明:SWARM星载GPS相位观测值残差RMS为7~10mm;径向、切向以及法向6h重叠轨道差值RMS均在1cm左右,3个方向均无明显的系统误差。通过与欧空局(ESA)发布的精密轨道进行对比分析,径向轨道差值RMS为2~5cm,切向轨道差值RMS为2~5cm,法向轨道差值RMS为2~4cm,3D轨道差值RMS为4~7cm;SWARM-B定轨精度优于SWARM-A与SWARM-C。因此,采用简化动力学法与本文提供的定轨策略进行SWARM卫星精密定轨是切实可行的,定轨结果良好且稳定,定轨精度达到厘米级。     

GPS卫星精密定轨中的摄动力分析

在介绍各种摄动模型的基础上,将IGS提供的SP3精密星历作为几何轨道,应用不同的摄动模型进行几何轨道平滑,求得卫星轨道的动力学参数,再用动力学参数积分求定卫星的轨道,将其与IGS提供的SP3精密星历进行比较,从而详细分析每一种摄动力对GPS轨道影响的量级,而且说明建立的GPS卫星轨道的摄动模型是比较准确的。     

基于OpenGL和IGS精密星历的GPS卫星轨道可视化

利用IGS精密星历提供的GPS卫星坐标,采用切比雪夫多项式对GPS卫星坐标进行拟合,最终在MFC的环境中运用OpenGL实现对GPS卫星轨道的三维可视化。通过对GPS卫星轨道的可视化,为GPS卫星状态的监测提供了更加直观的工具,对以后卫星导航定位的研究具有重要的意义。     

GPS卫星轨道改进与精密定位

使用GPS卫星进行定位的精度,除其它各种因素外,还要受到已知轨道精度的限制。当GPS星历精度对民用用户降低时,轨道改进便具有更大的重要性。作者在此提出了一个改进轨道精度的方法,该方法利用摄动理论来描述轨道特性。为了改进轨道,我们对卫星通过的初始条件进行了修正,修正后的轨道又可转而用来求得精密定位成果。本文给出了精密轨道改进和精密定位的数学模型及导出的平方差方程式,还概括了在加拿大上空进行局部卫星轨道改进的模拟方案,并给出了这项研究的结果。     

星载GPS低轨卫星定轨理论及方法研究

论文研究了星载GPS低轨卫星定轨技术的基本理论和方法,研制了星载GPS低轨卫星约化动力法定轨软件,针对约化动力法和推广卡尔曼滤波存在的问题,开展了星载GPS低轨卫星自适应事后和实时定轨研究,论文最后对星载GPS编队卫星相对定位技术进行了研究。主要工作及创新点概括如下：     

GRACE卫星非差精密定轨精度分析

随着星载GPS接收机性能和精密轨道、钟差产品精度的提高,星载GPS观测技术已成为确定CHAMP、GRACE和GOCE等低轨卫星精密轨道的重要手段。文章以GRACE卫星为例,分别利用非差弱动力法和非差运动学方法精密确定其轨道,并将结果和美国喷气动力实验室(JPL)事后精密轨道对比。结果表明:GRACE卫星非差弱动力法和非差运动学定轨精度均可达到厘米级;在使用相同的星历、钟差等产品时,弱动力法定轨精度略微优于运动学方法。此外,本文采用超快预报精密星历实时确定GRACE卫星轨道时精度也优于10cm。     

On the precision and accuracy of IGS orbits

In order to explore the precision and accuracy of International GNSS Service (IGS) orbits, we difference geocentric satellite positions midway between successive daily Final orbits for the period starting 5 November 2006, when the IGS switched its method of antenna calibration, through 31 December 2007. This yields a time series of orbit repeatabilities analogous to the classical geodetic test for position determinations. If we compare our average positional discontinuities to the official IGS accuracy codes, root-sum-squared (RSS) for each pair of days, we find the discontinuities are not well correlated with the predicted performance values. If instead the IGS weighted root-mean-square (WRMS) values from the Final combination long-arc analyses are taken as the measure of IGS accuracy, we find the position differences and long-arc values are correlated, but the long-arc values are exaggerated, particularly around eclipses, despite the fact that our day-boundary position differences apply to a single epoch each day and the long-arc analyses consider variations over a week. Our method is not well suited to probe the extent to which systematic effects dominate over random orbit errors, as indicated by satellite laser ranging residuals, but eclipsing satellites often display the most problematic behavior. A better metric than the current IGS orbit accuracy codes would probably be one based on the orbit discontinuities between successive days.     

基于Helmert变换的GPS动力学轨道平滑(英文)

Orbit fitting is used in many GPS applications. For example, in Precise Point Positioning (PPP), GPS orbits (SP3 orbits) are normally retrieved either from IGS or from one of its Analysis Centers (ACs) with 15 minutes’ sampling, which is much bigger than the normal observation sampling. Therefore, algorithms should be derived to fit GPS orbits to the observation time. Many methods based on interpolation were developed. Using these methods the orbits fit well at the sampling points. However, these methods ig...     

Orbit fitting based on Helmert transformation

Orbit fitting is used in many GPS applications. For example, in Precise Point Positioning (PPP), GPS orbits (SP3 orbits) are normally retrieved either from IGS or from one of its Analysis Centers (ACs) with 15 minutes’ sampling, which is much bigger than the normal observation sampling. Therefore, algorithms should be derived to fit GPS orbits to the observation time. Many methods based on interpolation were developed. Using these methods the orbits fit well at the sampling points. However, these methods ignore the physical motion model of GPS satellites. Therefore, the trajectories may not fit the true orbits at the periods in between 2 sampling epochs. To solve this problem, we develop a dynamic approach, in which a model based on Helmert transformation is developed in GPS orbit fitting. In this orbit fitting approach, GPS orbits at sampling points are treated as pseudo-observations. Thereafter, Helmert transformation is built up between the pseudo-observations and dynamically integrated orbits at each epoch. A set of Helmert parameters together with corrections of GPS initial orbits are then modeled as unknown parameters. Results show that the final fit orbits have the same precision as the IGS final orbits.     

广域增强系统广播星历模型分析

针对广域增强系统10参数广播星历模型的应用范围与应用性能问题,该文提出了综合参数动力学含义和拟合精度的模型分析方法。以GPS 16参数模型为参照对象,采用轨道坐标系3方向投影法,对10参数和16参数模型的摄动表达机理进行了研究。基于GEO、IGSO和MEO 3种卫星实际数据,通过长弧和短弧条件下的拟合精度分析,完成了10参数模型应用性能的全面评估。实验结果表明:10参数模型在长弧条件下的拟合性能不佳,4min弧长条件下,3种卫星拟合精度均能够满足基本导航、在航飞行与精密进近等应用需求。所提方法解决了10参数模型从GEO卫星向其他类型卫星的拓展问题。     

Dynamic orbit determination and gravity field model improvement from GPS, DORIS and Laser measurements on TOPEX/POSEIDON satellite

Summary. In the framework of the GRIM series of gravity field models, the CNES/GRGS GINS precise orbit determination software has been adapted to dynamic GPS data processing. That is simultaneous processing of all available observables (i.e. GPS, DORIS, Laser) and all available satellite orbits (i.e. GPS, TOPEX/POSEIDON) can now be performed. The TOPEX/POSEIDON (T/P) mission satellite is equipped with a GPS receiver, a DORIS receiver and a laser reflector that represents an unprecedented opportunity to compare and combine these three tracking systems to estimate orbital parameters and gravity field coefficients. Different combinations including : GPS + DORIS, DORIS + LASER, GPS + DORIS + LASER, have been tested and have shown small but systematic improvement in T/P orbit accuracy when GPS and DORIS data were processed simultaneously. Five tuned gravity field models have been generated by accumulating different combinations of T/P normal equations associated to the GPS, DORIS and Laser data. GPS data have a greater dynamic impact on gravity field spherical harmonics coefficient determination than DORIS and Laser data. Furthermore, the results obtained with the solutions including and T/P normal equations suggest that indeed these different tracking systems are somehow complementary in a dynamic sense. Received 30 March 1995; Accepted 19 September 1996     

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.     

Precise orbit determination for the FORMOSAT-3/COSMIC satellite mission using GPS

The joint Taiwan–US mission FORMOSAT-3/ COSMIC (COSMIC) was launched on April 17, 2006. Each of the six satellites is equipped with two POD antennas. The orbits of the six satellites are determined from GPS data using zero-difference carrier-phase measurements by the reduced dynamic and kinematic methods. The effects of satellite center of mass (COM) variation, satellite attitude, GPS antenna phase center variation (PCV), and cable delay difference on the COSMIC orbit determination are studied. Nominal attitudes estimated from satellite state vectors deliver a better orbit accuracy when compared to observed attitude. Numerical tests show that the COSMIC COM must be precisely calibrated in order not to corrupt orbit determination. Based on the analyses of the 5 and 6-h orbit overlaps of two 30-h arcs, orbit accuracies from the reduced dynamic and kinematic solutions are nearly identical and are at the 2–3 cm level. The mean RMS difference between the orbits from this paper and those from UCAR (near real-time) and WHU (post-processed) is about 10 cm, which is largely due to different uses of GPS ephemerides, high-rate GPS clocks and force models. The kinematic orbits of COSMIC are expected to be used for recovery of temporal variations in the gravity field.     

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.     

Pseudo-Stochastic Orbit Modeling Techniques for Low-Earth Orbiters

The Earth’s non-spherical mass distribution and atmospheric drag cause the strongest perturbations on very low-Earth orbiting satellites (LEOs). Models of gravitational and non-gravitational accelerations are utilized in dynamic precise orbit determination (POD) with GPS data, but it is also possible to derive LEO positions based on GPS precise point positioning without dynamical information. We use the reduced-dynamic technique for LEO POD, which combines the geometric strength of the GPS observations with the force models, and investigate the performance of different pseudo-stochastic orbit parametrizations, such as instantaneous velocity changes (pulses), piecewise constant accelerations, and continuous piecewise linear accelerations. The estimation of such empirical orbit parameters in a standard least-squares adjustment process of GPS observations, together with other relevant parameters, strives for the highest precision in the computation of LEO trajectories. We used the procedures for the CHAMP satellite and found that the orbits may be validated by means of independent SLR measurements at the level of 3.2 cm RMS. Validations with independent accelerometer data revealed correlations at the level of 95% in the along-track direction. As expected, the empirical parameters compensate to a certain extent for deficiencies in the dynamic models. We analyzed the capability of pseudo-stochastic parameters for deriving information about the mismodeled part of the force field and found evidence that the resulting orbits may be used to recover force field parameters, if the number of pseudo-stochastic parameters is large enough. Results based on simulations showed a significantly better performance of acceleration-based orbits for gravity field recovery than for pulse-based orbits, with a quality comparable to a direct estimation if unconstrained accelerations are set up every 30 s.     

GPS长距离和多测段定位中广播星历的改进方法

本文分析了广播星历误差对ＧＰＳ长基线和多测段定位结果的影响，由此提出了旨在减弱卫星轨道误差对于相对定位精度影响的一种简便而又实用的方法，即先按卫星运动的力学模型建立状态方程，其初始状态向量由某组广播星历得出，由每组广播星历建立观测方程，由数值积分得出的参考轨道由广播星历ｔｏｅ时刻的位置和速度观测值的最小二乘平差所得的改正后的轨道，不仅可消除各组广播星历间的不一致性，而且其精度也高于任何一组广播星历