共查询到19条相似文献，搜索用时 187 毫秒
1.
《测绘科学技术学报》2020,(2)
针对GPS卫星精密轨道和钟差插值对GRACE卫星定轨精度影响进行了分析,分别使用IGS(International GNSS Service)30 s间隔钟差、CODE(the Center for Orbit Determination in Europe)30和5 s间隔钟差以及15 min精密星历进行GRACE卫星定轨实验。结果表明:GPS轨道插值精度可以达到cm级,将15 min GPS轨道插值为30 s间隔利用9阶拉格朗日插值定轨结果精度最高,继续增加阶数定轨精度不会增加;利用CODE钟差计算GRACE非差运动学轨道,码伪距结果精度较IGS产品提高6%,载波相位运动学定轨结果和约化动力学定轨结果精度都提高10%左右;5 s间隔卫星钟数据对定轨结果改进并不明显。采用CODE间隔为30 s钟差进行GRACE运动学定轨的计算精度能满足cm级轨道的应用需求。 相似文献
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精密卫星钟差加密方法及其对星载GPS低轨卫星定轨精度影响 总被引：7，自引：0，他引：7
韩保民 《武汉大学学报(信息科学版)》2006,31(12):1075-1078
系统分析、比较了几种精密卫星钟差加密方法，研究了利用全球分布的IGS永久跟踪站的GPS观测数据估计高采样率卫星钟差参数的原理与方法，并将各种卫星钟差加密方法得到的结果与IGS数据分析中心估计的卫星钟差结果相比较。最后将不同加密方法得出的精密卫星钟差结果用于基于星载GPS双频非差观测值的CHAMP低轨卫星的定轨，并将不同方法得到的定轨精度进行比较。结果表明，利用地面跟踪站的GPS观测数据，可高精度、高密度地估计GPS卫星钟差，估计精度可达0．1～0．5ns。经地面GPS跟踪站数据估计的GPS卫星钟差，应用于基于PPP方法的低轨卫星定轨，其定轨精度在10cm以内。 相似文献
3.
《武汉大学学报(信息科学版)》2010,(6)
介绍了非差运动学精密定轨的基本原理,比较分析了精密星历和钟差以及导航星座空间几何构形对GRACE卫星非差运动学定轨的影响。数值分析表明,不同IGS精密轨道对应的GRACE卫星运动学轨道精度相当,而30s间隔和5s间隔钟差对应的径向定轨精度分别为3.8cm和3.4cm,说明高采样率的精密钟差有助于提高非差运动学精密定轨的精度。 相似文献
4.
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。 相似文献
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采用2015年5月24日—30日的Swarm星载GPS双频观测数据,基于Melbourne-Wübbena(MW)和消电离层线性组合,在精密单点定位技术的基础上,采用批处理最小二乘估计法对不同轨道高度的Swarm系列卫星进行非差运动学精密定轨。利用星载GPS相位观测值残差、与欧空局发布的简化动力学轨道对比,以及SLR检核3种方法对Swarm系列卫星非差运动学定轨结果进行精度评估。结果表明:①Swarm系列卫星星载GPS相位观测值残差RMS为6~7 mm;②与欧空局发布的简化动力学轨道进行求差,径向、切向及法向轨道差值RMS为2~4 cm;③与欧空局发布的运动学轨道进行求差,径向、切向及法向轨道差值RMS为1~2 cm;④SLR检核结果表明Swarm-A/B/C卫星轨道精度为3~4 cm。因此,采用非差运动学定轨方法与本文提供的定轨策略进行Swarm系列卫星精密定轨是切实可行的,定轨精度为厘米级。 相似文献
7.
《测绘科学技术学报》2013,(3)
利用BDS/GPS双模观测数据,研究了高精度北斗卫星精密定轨的实现方法,使用PANDA软件,结合"北斗卫星观测实验网"的实测数据,进行了精密定轨实验,结果表明:北斗卫星径向定轨精度能够达到优于10 cm的水平;其中,GEO三维定轨精度能够优于5 m,但沿迹方向存在系统偏差,IGSO/MEO三维定轨精度优于0.5 m。 相似文献
8.
IGS卫星钟差产品采样间隔对PPP精度的影响 总被引：1，自引：0，他引：1
使用IGS 5 min、30 s以及CODE最新发布的5 s间隔的精密卫星钟差产品分别进行了静态和动态精密单点定位(PPP)试验。结果表明,使用三种不同采样间隔的精密卫星钟差对静态PPP定位结果的影响很小,均能满足mm至cm级的静态定位精度,采样率更高的精密卫星钟差改正对静态定位结果无显著改善;对动态PPP定位,三种采样间隔的精密卫星钟差均能满足cm至dm级的定位精度,使用30 s间隔的精密卫星钟差较使用5 min间隔的精密卫星钟差,其定位精度提高了30%~50%,而使用5 s间隔的精密卫星钟差同使用30 s间隔的精密卫星钟差获得的定位精度基本一致。 相似文献
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单星GPS相位模糊度固定可以显著提升低轨卫星的定轨精度。目前,CNES/CLS、武汉大学和CODE 3家机构都已公开发布用于单星模糊度固定的GPS整数相位钟产品。本文首先利用整数相位钟方法实现单星模糊度固定,并应用于低轨卫星精密定轨中;然后,对比分析了不同机构提供的整数相位钟产品在低轨卫星单星模糊度固定和精密定轨中的应用性能;最后,通过对GRACE-FO编队卫星数据进行处理,发现基于不同机构产品的窄巷模糊度固定成功率都可以达到94%左右。不同机构产品获得的模糊度固定解轨道的SLR(satellite laser ranging)检核残差RMS约为0.9 cm,与模糊度浮点解的定轨结果相比,单星绝对轨道精度提高了约30%。在分别利用CNES/CLS、武汉大学和CODE产品实现单星模糊度固定后,双星相对轨道的KBR(K-band ranging)检核残差RMS分别从5.7、5.4和5.3 mm减小到2.1、2.0和1.5 mm。结果表明,不同整数相位钟产品在GRACE-FO卫星单星模糊度固定和精密定轨中的效果相当。 相似文献
12.
Phase center modeling for LEO GPS receiver antennas and its impact on precise orbit determination 总被引：12，自引：5，他引：7
Adrian Jäggi R. Dach O. Montenbruck U. Hugentobler H. Bock G. Beutler 《Journal of Geodesy》2009,83(12):1145-1162
Most satellites in a low-Earth orbit (LEO) with demanding requirements on precise orbit determination (POD) are equipped with
on-board receivers to collect the observations from Global Navigation Satellite systems (GNSS), such as the Global Positioning
System (GPS). Limiting factors for LEO POD are nowadays mainly encountered with the modeling of the carrier phase observations,
where a precise knowledge of the phase center location of the GNSS antennas is a prerequisite for high-precision orbit analyses.
Since 5 November 2006 (GPS week 1400), absolute instead of relative values for the phase center location of GNSS receiver
and transmitter antennas are adopted in the processing standards of the International GNSS Service (IGS). The absolute phase
center modeling is based on robot calibrations for a number of terrestrial receiver antennas, whereas compatible antenna models
were subsequently derived for the remaining terrestrial receiver antennas by conversion (from relative corrections), and for
the GNSS transmitter antennas by estimation. However, consistent receiver antenna models for space missions such as GRACE
and TerraSAR-X, which are equipped with non-geodetic receiver antennas, are only available since a short time from robot calibrations.
We use GPS data of the aforementioned LEOs of the year 2007 together with the absolute antenna modeling to assess the presently
achieved accuracy from state-of-the-art reduced-dynamic LEO POD strategies for absolute and relative navigation. Near-field
multipath and cross-talk with active GPS occultation antennas turn out to be important and significant sources for systematic
carrier phase measurement errors that are encountered in the actual spacecraft environments. We assess different methodologies
for the in-flight determination of empirical phase pattern corrections for LEO receiver antennas and discuss their impact
on POD. By means of independent K-band measurements, we show that zero-difference GRACE orbits can be significantly improved
from about 10 to 6 mm K-band standard deviation when taking empirical phase corrections into account, and assess the impact
of the corrections on precise baseline estimates and further applications such as gravity field recovery from kinematic LEO
positions. 相似文献
13.
Both static and kinematic testings are investigated by using IGS 5min, 30s and 5s-interval precise satellite clock products
in precise point positioning (PPP) solution. Test results show that the sampling rate of IGS satellite clock has very little
effect on the static PPP solution. All the three types of sampling intervals of precise satellite clock can satisfy mm-cm
level of positioning accuracy; higher sampling rate has no significant improvement for PPP solution. However, sampling rate
of satellite clock has a significant impact on the PPP solution in kinematic PPP. The higher the interval of satellite clock,
the better the accuracy achieved. The accuracy of kinematic PPP achieved by using 30s-interval precise satellite clock is
improved by nearly 30–50 percent with respect to the solution by using 5min-interval precise satellite clock, but using 5s
and 30s-interval satellite clock can almost produce the same accuracy of kinematic solution. Moreover, the use of precise
satellite clock products from different analysis centers may also produce more or less effect on the PPP solution. 相似文献
14.
Both static and kinematic testings are investigated by using IGS 5min, 30s and 5s-interval precise satellite clock products in precise point positioning (PPP) solution. Test results show that the sampling rate of IGS satellite clock has very little effect on the static PPP solution. All the three types of sampling intervals of precise satellite clock can satisfy mm-cm level of positioning accuracy; higher sampling rate has no significant improvement for PPP solution. However, sampling rate of satellite clock has a significant impact on the PPP solution in kinematic PPP. The higher the interval of satellite clock, the better the accuracy achieved. The accuracy of kinematic PPP achieved by using 30s-interval precise satellite clock is improved by nearly 30–50 percent with respect to the solution by using 5min-interval precise satellite clock, but using 5s and 30s-interval satellite clock can almost produce the same accuracy of kinematic solution. Moreover, the use of precise satellite clock products from different analysis centers may also produce more or less effect on the PPP solution. 相似文献
15.
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。 相似文献
16.
高精度、高可靠性的卫星轨道是实现低轨卫星精密应用的重要前提,而模糊度固定技术是提高卫星定轨精度的关键途径。研究了基于整数钟的星间单差模糊度固定原理和方法,并利用2019年4月—5月的两颗GRACE-FO（gravity recovery and climate experiment follow on）卫星数据（GRACE-C/D）系统评估了固定解对低轨卫星简化动力学和运动学定轨的精度提升效果。结果表明,两颗卫星简化动力学和运动学定轨的宽巷模糊度固定率均达到99%,而窄巷模糊度固定率在95%左右。对于简化动力学定轨,GRACE-C/D固定解轨道的重叠轨道的3D均方根误差（root mean square error, RMSE）分别从7.1 mm和7.4 mm减小到了4.2 mm和3.6 mm;卫星激光测距（satellite laser ranging, SLR）残差标准差（standard deviation, STD）分别从15.9 mm和14.4 mm降低到了10.8 mm和11.0 mm,精度提升了32%和24%;K波段测距残差RMSE从8.0 mm减小到2.9 mm,进一步表明固定解还能有效提升低轨卫星间相对位置精度。对于运动学定轨,与精密科学轨道产品互差3D RMSE,浮点解分别为37.5 mm和36.4 mm,固定解分别为27.7 mm和25.5 mm,精度提升约28%,SLR残差STD也减小了约20%。 相似文献
17.
Different types of GPS clock and orbit data provided by the International GPS Service (IGS) have been used to assess the accuracy
of rapid orbit determination for satellites in low Earth orbit (LEO) using spaceborne GPS measurements. To avoid the need
for reference measurements from ground-based reference receivers, the analysis is based on an undifferenced processing of
GPS code and carrier-phase measurements. Special attention is therefore given to the quality of GPS clock data that directly
affects the resulting orbit determination accuracy. Interpolation of clock data from the available 15 min grid points is identified
as a limiting factor in the use of IGS ultra-rapid ephemerides. Despite this restriction, a 10-cm orbit determination accuracy
can be obtained with these products data as demonstrated for the GRACE-B spacecraft during selected data arcs between 2002
and 2004. This performance may be compared with a 5-cm orbit determination accuracy achievable with IGS rapid and final products
using 5 min clock samples. For improved accuracy, high-rate (30 s) clock solutions are recommended that are presently only
available from individual IGS centers. Likewise, a reduced latency and more frequent updates of IGS ultra-rapid ephemerides
are desirable to meet the requirements of upcoming satellite missions for near real-time and precise orbit determination. 相似文献
18.
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. 相似文献
19.
Kinematic positions of Low Earth Orbiters based on GPS tracking are frequently used as pseudo-observations for single satellite gravity field determination. Unfortunately, the accuracy of the satellite trajectory is partly limited because the receiver synchronization error has to be estimated along with the kinematic coordinates at every observation epoch. We review the requirements for GPS receiver clock modeling in Precise Point Positioning (PPP) and analyze its impact on kinematic orbit determination for the two satellites of the Gravity Recovery and Climate Experiment (GRACE) mission using both simulated and real data. We demonstrate that a piecewise linear parameterization can be used to model the ultra-stable oscillators that drive the GPS receivers on board of the GRACE satellites. Using such a continuous clock model allows position estimation even if the number of usable GPS satellites drops to three and improves the robustness of the solution with respect to outliers. Furthermore, simulations indicate a potential accuracy improvement of the satellite trajectory of at least 40 % in the radial direction and up to 7 % in the along-track and cross-track directions when a 60-s piecewise linear clock model is estimated instead of epoch-wise independent receiver clock offsets. For PPP with real GRACE data, the accuracy evaluation is hampered by the lack of a reference orbit of significantly higher accuracy. However, comparisons with a smooth reduced-dynamic orbit indicate a significant reduction of the high-frequency noise in the radial component of the kinematic orbit. 相似文献