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1.
Phase center modeling for LEO GPS receiver antennas and its impact on precise orbit determination 总被引：7，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
2.
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
3.
J. Kouba 《GPS Solutions》2002,5(4):1-9
Since Selective Availability was permanently switched off on 7 May 2000, most of the GPS satellite clocks have been well behaved.
During a 24-h period precise satellite clock solutions, corrected for GPS conventional relativistic corrections, follow straight
lines within a few nanoseconds. The linear clock fit RMS for the best satellite clocks are well below the 1-ns level, which
is consistent with the nominal stability of the GPS frequency standards. Typically, the GPS satellite clocks show an Allan
variance at or below one part in 1011/100 s for the Cesium frequency standards and a few parts in 1012/100 s for the Rubidium frequency standards. These results correspond to clock RMSs for 15-min sampling at or below 3 and
0.3 ns, respectively. This already confirms experimentally that the conventional periodic relativity correction of the GPS
system, also adopted for all the IGS clock solution products, is precise and correct to 0.6 ns or better. To establish the
precision limits of the GPS conventional relativity treatment, the relativistic time transformations of GPS satellite frequency
and clocks are critically reviewed, taking into account all the contributions larger than the 10−18 (or 0.001 ns). The conventional GPS relativity treatment was found to be accurate, i. e., correctly modeling the actual relativistic
frequency (clock rate) effects of GPS satellites at about the 10−14 level. However, it is also affected by small periodic errors of the same magnitude. The integration of these small periodic
frequency relativistic errors gives the approximation errors of the conventional periodic relativistic clock correction with
amplitudes of about 0.1 ns and a predominant period equal to a half of the orbital period (∼ 6 h). These approximation errors
of the conventional GPS relativistic clock correction are at about the same level as the current precision of the IGS clock
solutions. ? 2002 Wiley Periodicals, Inc. 相似文献
4.
Cheinway Hwang Tzu-Pang Tseng Tingjung Lin Dražen Švehla Bill Schreiner 《Journal of Geodesy》2009,83(5):477-489
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. 相似文献
5.
Since the Selective Availability was turned off, the velocity and acceleration can be determined accurately with a single GPS receiver using raw Doppler measurements. The carrier-phase-derived Doppler measurements are normally used to determine velocity and acceleration when there is no direct output of the raw Doppler observations in GPS receivers. Due to GPS receiver clock drifts, however, a GPS receiver clock jump occurs when the GPS receiver clock resets itself (typically with 1 ms increment/decrement) to synchronize with the GPS time. The clock jump affects the corresponding relationship between measurements and their time tags, which results in non-equidistant measurement sampling in time or incorrect time tags. This in turn affects velocity and acceleration determined for a GPS receiver by the conventional method which needs equidistant carrier phases to construct the derived Doppler measurements. To overcome this problem, an improved method that takes into account, GPS receiver clock jumps are devised to generate non-equidistant-derived Doppler observations based on non-equidistant carrier phases. Test results for static and kinematic receivers, which are obtained by using the conventional method without reconstructing the equidistant continuous carrier phases, show that receiver velocity and acceleration suffered significantly from clock jumps. An airborne kinematic experiment shows that the greatest impact on velocity and acceleration reaches up to 0.2 m/s, 0.1 m/s2 for the horizontal component and 0.5 m/s, 0.25 m/s2 for the vertical component. Therefore, it can be demonstrated that velocity and acceleration measurements by using a standalone GPS receiver can be immune to the influence of GPS receiver clock jumps with the proposed method. 相似文献
6.
A technique for obtaining clock measurements from individual GNSS satellites at short time intervals is presented. The methodology developed in this study allows for accurate satellite clock stability analysis without an ultra-stable clock at the ground receiver. Variations in the carrier phase caused by the satellite clock are isolated using a combination of common GNSS carrier-phase processing techniques. Furthermore, the white phase variations caused by the thermal noise of the collection and processing equipment are statistically modeled and removed, allowing for analysis of clock performance at subsecond intervals. Allan deviation analyses of signals collected from GPS and GLONASS satellites reveal distinct intervals of clock noise for timescales less than 100 s. The clock data collected from GPS Block IIA, IIR, IIR-M, and GLONASS satellites reveal similar stability performance at time periods greater than 20 s. The GLONASS clock stability in the 0.6–10 s range, however, is significantly worse than GPS. Applications that rely on ultra-stable clock behavior from the GLONASS satellites at these timescales may therefore require high-rate corrections to estimate and remove oscillator-based errors in the carrier phase. 相似文献
7.
Estimation of Clock Stability Using GPS 总被引：2，自引：0，他引：2
The recent development of low-cost, high-precision oscillators has allowed many applications in various fields to become financially
feasible. The stability of an oscillator is ultimatively what determines its usefulness for a certain application, and is
therefore desirable to quantify. Current methods of evaluating stability require a direct comparison of the oscillator under
test (OUT) with amore stable reference oscillator, the cost of which often offsets the initial benefit of a low-cost device.
However, a relatively inexpensive Global Positioning System (GPS) receiver is capable of exploiting the highly stable GPS
time scale, thus obviating the need for an expensive reference oscillator. By allowing the OUT to drive a GPS receiver, and
processing the data with precise GPS orbits and clock corrections to eliminate the effects of selective availability (SA),
the time series of computed clock offsets provides a measure of the oscillator's stability relative to GPS time.
The use of GPS for assessing clock stability in the time domain is evaluated herein via the computation of Allan variance
values. Performance of one rubidium and three ovenized crystal oscillator are investigated. Results show the method is limited
to time intervals less than about two seconds or longer than about 300 seconds, where the effects of measurement noise and
residual SA is less pronounced. ? 2000 John Wiley & Sons, Inc. 相似文献
8.
Generation of a consistent absolute phase-center correction model for GPS receiver and satellite antennas 总被引：26，自引：16，他引：10
Ralf Schmid Peter Steigenberger Gerd Gendt Maorong Ge Markus Rothacher 《Journal of Geodesy》2007,81(12):781-798
The development and numerical values of the new absolute phase-center correction model for GPS receiver and satellite antennas, as adopted by the International GNSS (global navigation satellite systems) Service, are presented. Fixing absolute receiver antenna phase-center corrections to robot-based calibrations, the GeoForschungsZentrum Potsdam (GFZ) and the Technische Universität München reprocessed more than 10 years of GPS data in order to generate a consistent set of nadir-dependent phase-center variations (PCVs) and offsets in the z-direction pointing toward the Earth for all GPS satellites in orbit during that period. The agreement between the two solutions estimated by independent software packages is better than 1 mm for the PCVs and about 4 cm for the z-offsets. In addition, the long time-series facilitates the study of correlations of the satellite antenna corrections with several other parameters such as the global terrestrial scale or the orientation of the orbital planes with respect to the Sun. Finally, completely reprocessed GPS solutions using different phase-center correction models demonstrate the benefits from switching from relative to absolute antenna phase-center corrections. For example, tropospheric zenith delay biases between GPS and very long baseline interferometry (VLBI), as well as the drift of the terrestrial scale, are reduced and the GPS orbit consistency is improved. 相似文献
9.
Oliver Montenbruck Miquel Garcia-Fernandez Yoke Yoon Steffen Schön Adrian Jäggi 《GPS Solutions》2009,13(1):23-34
Phase center variations of the receiver and transmitter antenna constitute a remaining uncertainty in the high precision orbit
determination (POD) of low Earth orbit (LEO) satellites using GPS measurements. Triggered by the adoption of absolute phase
patterns in the IGS processing standards, a calibration of the Sensor Systems S67-1575-14 antenna with GFZ choke ring has
been conducted that serves as POD antenna on various geodetic satellites such as CHAMP, GRACE and TerraSAR-X. Nominal phase
patterns have been obtained with a robotic measurement system in a field campaign and the results were used to assess the
impact of receiver antenna phase patterns on the achievable positioning accuracy. Along with this, phase center distortions
in the actual spacecraft environment were characterized based on POD carrier phase residuals for the GRACE and TerraSAR-X
missions. It is shown that the combined ground and in-flight calibration can improve the carrier phase modeling accuracy to
a level of 4 mm which is close to the pure receiver noise. A 3.5 cm (3D rms) consistency of kinematic and reduced dynamic
orbit determination solutions is achieved for TerraSAR-X, which presumably reflects the limitations of presently available
GPS ephemeris products. The reduced dynamic solutions themselves match the observations of high grade satellite laser ranging
stations to 1.5 cm but are potentially affected by cross-track biases at the cm-level. With respect to the GPS based relative
navigation of TerraSAR-X/TanDEM-X formation, the in-flight calibration of the antenna phase patterns is considered essential
for an accurate modeling of differential carrier phase measurements and a mm level baseline reconstruction.
相似文献
| Oliver MontenbruckEmail: |
10.
针对GPS卫星钟差及观测数据间隔对LEO卫星运动学和约化动力学定轨的影响问题进行了分析,并使用CODE（the Center for Orbit Determination in Europe）30 s、5 s间隔GPS卫星钟差分别进行了30 s和10 s间隔观测数据的LEO卫星定轨实验。结果表明,使用5 s间隔卫星钟差（10 s间隔观测数据）相比30 s间隔卫星钟差（30 s间隔观测数据）进行GRACE卫星精密定轨,约化动力学定轨精度提高了16%,运动学定轨精度提高了8.8%;使用30 s间隔卫星钟差和10 s间隔观测数据的定轨精度最低;对于30 s间隔观测数据,使用30 s或5 s间隔卫星钟差的定轨精度基本一致。 相似文献
11.
We have inferred the temperature sensitivity of Dorne Margolin choke ring antennas by direct estimation from differential
clock estimates for two GPS sites separated by 2400 km. At each site, the cable and receiver systems are very well isolated
from environmental variations. By direct comparison of the observed clock variations between these sites with local temperature
measurements, empirical temperature coefficients for each system have been estimated. These thermal coefficients most likely
apply to the only uncontrolled components of the systems, the Dorne Margolin choke ring antennas. Based on these results,
the short-term (diurnal) stability of the antennas appears to be better than 2 ps/°C. The possibility that longer-term effects
exist due to sensitivity in the daily average of the pseudorange observations has not been tested and cannot be excluded.
? 2001 John Wiley & Sons, Inc. 相似文献
12.
Ziqian Wu Shanshi Zhou Xiaogong Hu Li Liu Tao Shuai Yonghui Xie Chengpan Tang Junyang Pan Lingfeng Zhu Zhiqiao Chang 《GPS Solutions》2018,22(2):43
Various types of onboard atomic clocks such as rubidium, cesium and hydrogen have different frequency accuracies and frequency drift rate characteristics. A passive hydrogen maser (PHM) has the advantage of low-frequency drift over a long period, which is suitable for long-term autonomous satellite time keeping. The third generation of Beidou Satellite Navigation System (BDS3) is equipped with PHMs which have been independently developed by China for their IGSO and MEO experimental satellites. Including Galileo, it is the second global satellite navigation system that uses PHM as a frequency standard for navigation signals. We briefly introduce the PHM design at the Shanghai Astronomical Observatory (SHAO) and detailed performance evaluation of in-orbit PHMs. Using the high-precision clock values obtained by satellite-ground and inter-satellite measurement and communication systems, we analyze the frequency stability, clock prediction accuracy and clock rate variation characteristics of the BDS3 experimental satellites. The results show that the in-orbit PHM frequency stability of the BDS3 is approximately 6 × 10?15 at 1-day intervals, which is better than those of other types of onboard atomic clocks. The BDS3 PHM 2-, 10-h and 7-day clock prediction precision values are 0.26, 0.4 and 2.2 ns, respectively, which are better than those of the BDS3 rubidium clock and most of the GPS Block IIF and Galileo clocks. The BDS3 PHM 15-day clock rate variation is ? 1.83 × 10?14 s/s, which indicates an extremely small frequency drift. The 15-day long-term stability results show that the BDS3 PHM in-orbit stability is roughly the same as the ground performance test. The PHM is expected to provide a highly stable time and frequency standard in the autonomous navigation case. 相似文献
13.
将在一定时空限定范围内的不同低轨卫星COSMIC、GRACE、CHAMP、FY3C的电离层掩星电子密度剖面定义为一个掩星对来对比分析不同类型掩星电离层产品。结果表明：COSMIC掩星对之间的电子密度剖面整体轮廓符合得很好，电子密度剖面主要在250 km以下和500 km以上存在较大的偏差，250~500 km的电子密度整体偏差较小，统计得到的COSMIC掩星对的电子密度参量NmF2和hmF2的相关系数能分别达到0.99和0.97，具有高度相关性，不同COSMIC卫星之间没有明显的系统误差；COSMIC、GRACE、CHAMP和FY3C不同低轨卫星间的电子密度剖面略有差异，通过统计电子密度参量NmF2和hmF2之间的相关系数，COSMIC和CHAMP的相关系数分别为0.95和0.86，COSMIC和GRACE的相关系数分别为0.98和0.94，COSMIC和FY3C的相关系数分别为0.96和0.92，不同掩星类型之间的电子密度参量之间也具有高度相关性，验证了不同卫星任务GPS掩星电离层剖面的一致性。 相似文献
14.
日本准天顶卫星系统（QZSS）卫星通过L波段实时播发高频全球卫星导航系统（GNSS）精密轨道和钟差产品,为GNSS导航用户提供实时精密单点定位（PPP）服务. 本文以JAXA MADOCA数据中心提供的1 s采样率GPS卫星钟差数据为研究对象,首先采用阿伦方差对卫星钟差的短期稳定性进行评估;然后分别采用一阶多项式、二阶多项式和灰色模型对高频钟差产品进行建模,在5 s,10 s和30 s的拟合窗口内预报后续10 s内钟差,并基于预报残差的均方根误差（RMS）评定不同类型GPS卫星钟差产品的短期预报精度. 基于2020年1月1日-21日连续21天的实时高频钟差统计分析结果表明,不同型号的GPS卫星钟差1 s,5 s和10 s的短期稳定性均能达到10-12量级;对比预报精度显示,10 s以内的拟合窗口采用最简单的一阶多项式最为稳定可靠,10 s延迟预报RMS精度可控制在0.1 ns以内;若采用30 s的拟合窗口,考虑钟差频漂特性的二阶多项式则更为稳定可靠,预报钟差的RMS精度能达到0.15 ns以内．由此可见,本文基于MADOCA-LEX钟差产品的实时预报精度可以满足厘米级PPP的需求． 相似文献
15.
Cheinway Hwang Tzu-Pang Tseng Ting-Jung Lin Dražen Švehla Urs Hugentobler Benjamin Fong Chao 《GPS Solutions》2010,14(1):121-131
The precise orbit determination antennas of F3/C and GRACE-A satellites are from the same manufacturer, but are installed
in different configurations. The current orbit accuracy of F3/C is 3 cm at arcs with good GPS data, compared to 1 cm of GRACE,
which has a larger ratio of usable GPS data. This paper compares the qualities of GPS observables from F3/C and GRACE. Using
selected satellites and time spans, the following average values for the satellite F3/C and satellite A of GRACE are obtained:
multipath effect on the pseudorange P1, 0.78 and 0.38 m; multipath effect on the pseudorange P2, 1.03 and 0.69 m; occurrence
frequency of cycle slip, 1/29 and 1/84; standard error of unit weight, 4 and 1 cm; dynamic–kinematic orbit difference, 10
and 2 cm. For gravity determination using F3/C GPS data, a careful selection of GPS data is critical. With six satellites
in orbit, F3/C’s large amount of GPS data will make up the deficiency in data quality. 相似文献
16.
首次搭载GPS/BDS双模接收机全球导航卫星掩星探测仪(GNOS)的风云三号C星于2013年9月23日的成功发射,为研究低轨卫星对BDS定轨增强提供了便利。本文首先对低轨卫星GNOS搭载的GPS/BDS双模接收机的观测数据进行统计,并分析了伪距测量精度。然后在全球测站、区域测站两种布局情况下,对无GNOS的BDS单系统定轨、无GNOS的GPS/BDS双系统定轨、有GNOS的BDS单系统定轨增强、有GNOS的GPS/BDS双系统定轨增强4种方案进行北斗轨道及钟差比较分析。结果表明,GNOS对北斗卫星轨道增强在全球测站下,GEO卫星切向精度提升最为显著,提升程度达60%,其次是法向和其他类型卫星切向,部分弧段个别GEO卫星径向精度稍有下降。双系统定轨增强中可视弧段钟差重叠精度RMS值有0.1ns量级改善。7个国内测站区域监测网的定轨试验中对轨道进行了预报,结果表明GNOS对北斗GEO卫星轨道预报精度切向提升达85%,其余方向及卫星有较大改善,平均21.7%。可视弧段钟差重叠精度RMS值有0.5ns量级改善。 相似文献
17.
为探究重力场恢复与气候实验(gravity recovery and climate experiment,GRACE)卫星与全球定位系统(global positioning system,GPS)两种独立技术获取的因陆地水储量变化引起的地壳垂向季节性位移的一致性,选取澳大利亚27个GPS站点5～10 a的高程时间序... 相似文献
18.
由于天线本身的特性及机械加工等原因,GPS卫星和接收机天线相位中心与其几何中心不重合,从而产生相位中心偏差。某些类型的天线该偏差甚至可达数cm,直接影响高精度GPS测量的精确可靠性[1]。讨论了GAMIT软件在高精度GPS数据处理中进行天线相位中心改正的原理、方法和策略,结合美国IGS观测站及南加州区域站观测数据,对改正方法及策略进行了实验对比与分析。结果表明:对接收机天线相位中心和卫星天线相位中心采用模型改正,而卫星天线相位中心偏移不改正,所得到的基线解算结果较好[2];地面接收机天线方位角的变化对U方向的基线解算结果有较大影响,在高精度GPS测量中,必须进行天线方位角的变化改正。 相似文献
19.
GPS高精度时间／频率同步设备设计和实现 总被引：1，自引：0，他引：1
研究分析了GPS接收机的定时特性，以及高精度时间／频率同步设备对GPS定时信号丢失后的指标要求，提出了GPS定时信号的滑动平均滤波算法和信号丢失后的保持算法，取得了频率稳定度优于1×10^-11／天和无时间漂移误差的成果，初步实现铯原子频标的性能，满足时间同步精度和频率稳定度的需求。 相似文献
20.
Min Li Wenwen Li Chuang Shi Kecai Jiang Xiang Guo Xiaolei Dai Xiangguang Meng Zhongdong Yang Guanglin Yang Mi Liao 《Journal of Geodesy》2017,91(11):1313-1327
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. 相似文献