共查询到19条相似文献，搜索用时 375 毫秒
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以GRACE卫星为例,分析比较利用SLR观测资料进行卫星定轨时,采用不同大气密度模型对GRACE卫星定轨精度的影响;将定轨结果与采用GPS的定轨结果进行比较,分析与GPS定轨结果的差异。实验证明,大气密度模型的选择对定轨结果的影响很明显,同时,比较了基于SLR的定轨结果与采用GPS的定轨结果,发现大气密度模型采用DTM的情况与采用GPS的轨道差异最小,差异的量级为米级。 相似文献
2.
针对GPS、SLR和DORIS三种不同手段的各自定轨精度问题,本文基于不同的轨道评估方法进行了深入分析。以JASON-2卫星为例,分析了姿态模型误差及其对定轨精度的影响,分别讨论了GPS、SLR和DORIS的定轨策略和定轨精度,并基于轨道评估结果进行了轨道叠加。基于实测数据进行了试验,试验结果表明,JASON-2卫星姿态模型误差对DORIS、GPS和SLR轨道影响分别为0.040、0.036和0.033m;DORIS定轨结果优于GPS和SLR,SLR定轨精度最差;基于SLR验证和轨道重叠结果加权,对GPS、SLR和DORIS轨道进行轨道叠加,其精度一致,通过与JPL轨道比较,其径向精度为2cm。 相似文献
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采用HY2A卫星2013年2月的实测数据,研究了GPS、星载多谱勒无线电定轨定位系统(DORIS)及卫星激光测距(SLR)三种观测数据的单独和联合定轨问题。通过与法国CNES的精密轨道数据比较发现:分别采用GPS、DORIS和SLR数据进行单独定轨,GPS数据确定轨道的径向平均精度为1.3cm,三维位置约为6.2cm;DORIS定轨的径向平均精度为1.6cm,比GPS结果略差;SLR确定轨道的径向平均精度为2.3cm。用GPS、DORIS和SLR三种数据联合定轨,确定轨道的径向平均精度为1.2cm,三维位置约为6.5cm。与星载GPS定轨结果比较,三种观测数据的联合定轨在提高卫星轨道确定精度上不明显,但联合定轨有利于保持计算轨道精度相对稳定。用站星间高度角大于60°的SLR数据检验GPS/DORIS联合确定的轨道,两者在测距方向的均方差为2.5cm,可见基于HY2A的观测数据可以实现cm级的定轨需求。 相似文献
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本文探讨了利用星载GPS数据实现平方根推广卡尔曼滤波(SR-EKF)定轨的方法,采用SR-EKF对两颗GRACE卫星进行了定轨试验计算,并将计算结果与Bernese5.0的计算结果进行了比较,比较分析表明:采用SR-EKF方法进行GRACE卫星定轨可以得到优于10cm的定轨精度;经验力参数可以平衡几何观测信息和动力模型信息,但增大了观测异常对定轨结果的影响;对位置和速度进行噪声补偿可以减弱观测异常对定轨结果的影响,但有可能使轨道出现系统性偏差。 相似文献
6.
重力卫星的星载GPS精密定轨 总被引：3，自引：1，他引：2
利用CHAMP和GRACE卫星的实测数据,研究了重力卫星的精密定轨问题,并针对几何法精密定轨方法给出了一种有效的星载数据编辑策略;在PANDA软件的基础上,处理了101 d的实测数据;通过与不同机构卫星轨道的比较、激光测距观测值检验以及重力场模型恢复等外部检核的方式,分析了卫星轨道的精度.结果显示,本文的简化动力学轨道的精度为2～3 cm;几何学轨道的定轨精度为3～4 cm,适用于重力场模型的解算. 相似文献
7.
利用GRACE卫星2015年1月1日至7日的星载GPS观测数据,基于卫星简化动力学定轨方法和事后批处理定轨模式,利用24小时弧段进行精密定轨。采用多种手段进行评价定轨精度,通过分析,观测值定轨残差稳定在7mm,与德国地学中心(GFZ)发布的事后精密轨道在径向、切向、法向的RMS值分别是3cm,2cm,3cm,利用SLR检核轨道精度优于4cm。结果表明,使用简化动力学定轨可实现低轨卫星的cm级高精度定轨。 相似文献
8.
《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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采用星载GPS观测数据与简化动力学定轨方法,在方程中引入伪随机脉冲参数,从而实现对Swarm卫星的精密定轨. 详细分析了不同阶次的GOCO06s地球重力场模型对Swarm卫星简化动力学定轨精度的影响,对比了PGM2000a、EIGEN-2、EGM2008以及GECO重力场模型展开到100阶次时Swarm卫星解算的轨道精度. 结果表明:当GOCO06s地球重力场模型阶次处于30～100阶次时,Swarm-A、Swarm-B和Swarm-C卫星在径向、切向、法向上的定轨精度随着GOCO06s阶次的不断增加而越来越高,而在高于100阶次时,定轨精度基本稳定,且在各方向定轨精度优于3 cm. 此外,采用100阶次GECO、EGM2008和GOCO06s模型对三颗Swarm卫星进行定轨,解算的轨道精度相当,且要高于同阶次其他重力场模型的定轨结果. 相似文献
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基于重力场信号的频谱特性建立了SST-hl加速度计和星载GPS等有效载荷的解析误差分析模型.以CHAMP卫星的相关技术指标为例,对卫星高度、加速度计精度和GPS定轨精度等技术指标与恢复重力场的性能作了模拟分析.将模拟分析结果与EGM96和EIGEN-CHAMP03S模型进行了比较,验证了解析模拟分析模型的有效性. 相似文献
11.
Zhigui Kang Byron Tapley Srinivas Bettadpur John Ries Peter Nagel Rick Pastor 《Journal of Geodesy》2006,80(6):322-331
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. 相似文献
12.
利用GRACE和SWARM重力卫星星载GPS观测数据,基于简化动力学方法进行精密定轨,通过相位观测值残差分析、重叠轨道对比和科学轨道对比进行轨道精度检核。GRACE和SWARM卫星相位观测值残差RMS值稳定在6 mm左右,重叠轨道对比差值RMS在径向、切向和法向均优于1.24 cm;通过与GFZ和ESA提供的GRACE卫星与SWARM卫星精密轨道对比,GRACE卫星简化动力学轨道在R,T,N方向的轨道精度分别达到1.3 cm、2.1 cm和1.3 cm;SWARM卫星简化动力学轨道在径向、切向和法向的轨道精度分别达到0.8 cm、1.3 cm和1.6 cm。实验表明,基于简化动力学方法,GRACE和SWARM卫星定轨精度均到达厘米级。 相似文献
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Validation of GOCE gravity field models by means of orbit residuals and geoid comparisons 总被引：6，自引：3，他引：3
Three GOCE-based gravity field solutions have been computed by ESA’s high-level processing facility and were released to the
user community. All models are accompanied by variance-covariance information resulting either from the least squares procedure
or a Monte-Carlo approach. In order to obtain independent external quality parameters and to assess the current performance
of these models, a set of independent tests based on satellite orbit determination and geoid comparisons is applied. Both
test methods can be regarded as complementary because they either investigate the performance in the long wavelength spectral
domain (orbit determination) or in the spatial domain (geoid comparisons). The test procedure was applied to the three GOCE
gravity field solutions and to a number of selected pre-launch models for comparison. Orbit determination results suggest,
that a pure GOCE gravity field model does not outperform the multi-year GRACE gravity field solutions. This was expected as
GOCE is designed to improve the determination of the medium to high frequencies of the Earth gravity field (in the range of
degree and order 50 to 200). Nevertheless, in case of an optimal combination of GOCE and GRACE data, orbit determination results
should not deteriorate. So this validation procedure can also be used for testing the optimality of the approach adopted for
producing combined GOCE and GRACE models. Results from geoid comparisons indicate that with the 2 months of GOCE data a significant
improvement in the determination of the spherical harmonic spectrum of the global gravity field between degree 50 and 200
can be reached. Even though the ultimate mission goal has not yet been reached, especially due to the limited time span of
used GOCE data (only 2 months), it was found that existing satellite-only gravity field models, which are based on 7 years
of GRACE data, can already be enhanced in terms of spatial resolution. It is expected that with the accumulation of more GOCE
data the gravity field model resolution and quality can be further enhanced, and the GOCE mission goal of 1–2 cm geoid accuracy
with 100 km spatial resolution can be achieved. 相似文献
15.
应用GRACE卫星数据反演高精度静态地球重力场是大地测量学界的热点之一。考虑到经典动力学法线性化误差随弧长拉长而迅速增长,本文以GRACE卫星轨道观测值为初值的线性化方法,建立了应用GRACE卫星轨道和星间距离变率反演地球重力场的改进动力学法理论模型。利用2003年1月至2010年12月的GRACE卫星姿态、轨道、星间距离变率和非保守力加速度等观测数据,解算了一个180阶次的无约束全球静态重力场模型Tongji-Dyn01s和一个采用Kaula规则约束的全球重力场模型Tongji-Dyn01k。与国际不同机构最新发布的纯GRACE数据解算的重力场模型(包括AIUB-GRACE03S、GGM05S、ITSG-Grace2014k和Tongji-GRACE01)进行比较,并利用DTU13海洋重力异常和GPS/水准高程异常进行外部检核,结果表明,Tongji-Dyn01s与国际最新模型精度处于同一水平,然而Tongji-Dyn01k模型总体上更加靠近EIGEN6C2重力场模型。 相似文献
16.
Simulation study of a follow-on gravity mission to GRACE 总被引：9，自引：3，他引：6
The gravity recovery and climate experiment (GRACE) has been providing monthly estimates of the Earth’s time-variable gravity
field since its launch in March 2002. The GRACE gravity estimates are used to study temporal mass variations on global and
regional scales, which are largely caused by a redistribution of water mass in the Earth system. The accuracy of the GRACE
gravity fields are primarily limited by the satellite-to-satellite range-rate measurement noise, accelerometer errors, attitude
errors, orbit errors, and temporal aliasing caused by un-modeled high-frequency variations in the gravity signal. Recent work
by Ball Aerospace & Technologies Corp., Boulder, CO has resulted in the successful development of an interferometric laser
ranging system to specifically address the limitations of the K-band microwave ranging system that provides the satellite-to-satellite
measurements for the GRACE mission. Full numerical simulations are performed for several possible configurations of a GRACE
Follow-On (GFO) mission to determine if a future satellite gravity recovery mission equipped with a laser ranging system will
provide better estimates of time-variable gravity, thus benefiting many areas of Earth systems research. The laser ranging
system improves the range-rate measurement precision to ~0.6 nm/s as compared to ~0.2 μm/s for the GRACE K-band microwave
ranging instrument. Four different mission scenarios are simulated to investigate the effect of the better instrument at two
different altitudes. The first pair of simulated missions is flown at GRACE altitude (~480 km) assuming on-board accelerometers
with the same noise characteristics as those currently used for GRACE. The second pair of missions is flown at an altitude
of ~250 km which requires a drag-free system to prevent satellite re-entry. In addition to allowing a lower satellite altitude,
the drag-free system also reduces the errors associated with the accelerometer. All simulated mission scenarios assume a two
satellite co-orbiting pair similar to GRACE in a near-polar, near-circular orbit. A method for local time variable gravity
recovery through mass concentration blocks (mascons) is used to form simulated gravity estimates for Greenland and the Amazon
region for three GFO configurations and GRACE. Simulation results show that the increased precision of the laser does not
improve gravity estimation when flown with on-board accelerometers at the same altitude and spacecraft separation as GRACE,
even when time-varying background models are not included. This study also shows that only modest improvement is realized
for the best-case scenario (laser, low-altitude, drag-free) as compared to GRACE due to temporal aliasing errors. These errors
are caused by high-frequency variations in the hydrology signal and imperfections in the atmospheric, oceanographic, and tidal
models which are used to remove unwanted signal. This work concludes that applying the updated technologies alone will not
immediately advance the accuracy of the gravity estimates. If the scientific objectives of a GFO mission require more accurate
gravity estimates, then future work should focus on improvements in the geophysical models, and ways in which the mission
design or data processing could reduce the effects of temporal aliasing. 相似文献
17.
刘基余 《武汉大学学报(信息科学版)》2005,30(10):870-872,880
依据地月激光测距的成功实践和对卫星激光定轨的基础研究,提出了用地面对嫦娥卫星作激光测距的方法,高精度地测定嫦娥卫星绕月飞行时的实时在轨位置,论述了多站激光定轨和单站激光定轨的解算数模。 相似文献
18.
GOCE卫星是首颗搭载高精度梯度仪,通过加速度计差分测量确定地球重力场的现代重力卫星。该卫星设计为无阻尼飞行状态（沿轨方向）,加速度计并未安置在卫星质心,这些特点使得GOCE与标准的卫星跟踪卫星重力测量模式有着显著的区别。本文首先指出GOCE任务中普通模式加速度校准存在不严密性问题,并提出了分别校准6个加速度计,分离偏差参数的方案。利用GOCE任务期内的几何法精密轨道,采用动力法完成校准,并分析了无阻尼控制的效果,发现：①虽然GOCE所在轨道高度的中性大气密度较GRACE高两到三个量级,但GOCE卫星在沿轨方向的残余非保守力比GRACE卫星的对应分量小一个量级,充分显示了无阻尼控制系统的补偿效果;②通过精密轨道内插的轨道速度与动力法轨道速度的比较可以得出,卫星无阻尼控制系统对GOCE卫星速度的显著影响;③计算了GOCE卫星所受的非保守力。获得了GOCE任务期间的加速度计校准参数,并讨论了利用其辅助重力梯度仪数据预处理的可能方法。 相似文献
19.
本文利用2002年4月至2010年10月的Lageos1和Lageos2两颗激光卫星观测数据、GRACE以及地球物理模型三种独立的方法计算地球低阶重力场系数J 的变化,根据大气压强数据计算 J 时分别按反变气压计（IB）和非反变气压计(NIB)两种假设进行计算。通过分析 J 的季节特性表明,大气在NIB假设下得到的周年振幅比在IB假设下得到的振幅大3倍左右,相位相差47°;大气和陆地水的质量变化对 J 周年变化的贡献占主导地位,海洋的影响最小;大气、海洋和陆地水得到 J 半年振幅和相位值与SLR得到的振幅和相位值吻合较差,尤其是在IB假设下大气得到的结果与SLR结果相差最大; SLR、GRACE和地球物理模型三种独立方法得到的 J 周年项之间吻合相对较好,GRACE得到的周年振幅比SLR得到的周年振幅大50%左右, SLR观测得到的 J 周年振幅介于在NIB和IB两种假设下地球物理模型得到的结果之间;GRACE与SLR得到的 J 半年项的振幅相同,在IB假设下AOW得到的 J 半年振幅和相位与SLR结果差异最大。 相似文献