共查询到19条相似文献，搜索用时 171 毫秒
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GPS精密星历插值方法的比较研究 总被引：17，自引：4，他引：17
GPS高精度测量中通常需要对GPS精密星历进行轨道插值，本文分别采用拉格朗日插值、切比雪夫多项式拟合以及线性逐次Neville插值三种方法对GPS卫星轨道进行了插值，比较了三种方法的特性及插值结果，得出了一些有益结论。 相似文献
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基于拉格朗日插值方法的GPS IGS精密星历插值分析 总被引：2，自引：0，他引：2
GPS数据处理中,为使用IGS精密星历获取GPS卫星精确的、更高采样率的轨道位置,必须要对精密星历进行插值.文中介绍拉格朗日插值方法的基本原理,并对其插值结果进行详细的分析讨论,得出几点有益结论. 相似文献
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利用地基GPS估计PWV（precipitable water vapor）时,除GPS观测数据外,GPS测站地表的气温和气压也是必要参数。针对我国多数GPS网并未配备相应的气象传感器的情况,利用美国环境预报中心气候预报系统第2版提供的逐6 h产品,并顾及测站高程转换时的平均海平面高改正,提出一种GPS测站气象参数的插值新方法。以香港卫星定位参考站网实测GPS数据进行试验研究,结果表明,平均海平面高对地表气压的插值结果影响较大,而对地表气温的插值结果影响较小;经平均海平面高改正后,地表气压插值结果的平均均方根误差（RMSE）为1.61 hPa,地表气温插值结果的平均RMSE为1.93 K;由插值气象参数估计的PWV的平均RMSE为2.76 mm,验证了所提方法的有效性。 相似文献
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《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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王解先 《地球空间信息科学学报》2009,12(2):95-99
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... 相似文献
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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. 相似文献
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研究GPS在动力学环境下的网定位,对我国来说具有很大的吸引力。在GPS定位实践中,动力法及半动力法的轨道改进定位方式都具有广泛的应用,但前者概括了卫星定位中最一般的动力学问题。因此,本文归纳和建立了相应的动力法定位模型,包括轨道状态方程、地面测站的状态方程及观测方程。简要介绍了更能反映卫星定位问题统计和力学本质的最优滤波和最优控制的估计方法。最后给出了事后轨道估计的最佳平滑方程。 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
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For precise real time or near real time differential GPS positioning in a wide or global area, precise GPS orbits or, alternatively,
precise orbital corrections with respect to a reference orbit, such as GPS broadcast ephemerides, must be used. This work
tests orbit interpolation methods, in order to represent the GPS orbits and orbital corrections accurately and efficiently
for these and other GPS applications. For precise GPS orbits given in the SP3 format at the 15 min interval, numerical tests
were conducted using Lagrange and Chebyshev as well as trigonometric polynomial functions. The results have demonstrated that
the 19- or 20-term trigonometric function is apparently the most efficient interpolator for a 12 h GPS orbital arc, achieving
1 cm level 3D interpolation accuracy that can meet the requirements of most precise applications. The test results also demonstrated
that the 9-term trigonometric function always yields optimal interpolation for a 2 h GPS orbit arc, in terms of interpolation
errors, compared to the results when using a different number of terms for the same function or one of the other tested polynomial
functions. This is evident from the minimal performance degradation when using the 9-term trigonometric function to interpolate
near or at the end of a data interval. By limiting interpolation to the center 15 min to 1.5 h of a 2 h orbit arc, thereby
eliminating the need to interpolate near the ends of that interval, users can opt for more terms (11 and 13) or different
interpolators to further improve interpolation accuracy. When interpolating the orbital corrections with respect to the GPS
broadcast ephemeris, all the tested interpolation functions of 3- to 9-term yield the same suitably accurate results. Therefore,
a 3- to 5-term trigonometric function is arguably sufficiently accurate and more efficient for GPS orbital correction messaging
in wide area and real time positioning. 相似文献
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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
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多面函数拟合法转换GPS高程 总被引：13，自引：0，他引：13
金时华 《测绘与空间地理信息》2005,28(6):44-47
对GPS在高程方面的应用现状作了简单的介绍,综述近年来用GPS求定正常高的几种方法,即多项曲线拟合、多项式曲面拟合、多面函数曲面拟合、加权均值法、非参数回归法和高程异常变化梯度法、固定边界三次样条插值法、线性移动拟事法、神经网络法、非格网GPS散点数据考虑地形改正法。对GPS高程测量基本原理和基本方法进行了讨论,提出根据测区的实际情况选择不同的GPS高程转换方法,综合利用GPS点的高差和高程观测值拟合高程异常的方法,利用多面函数来拟合似大地水准面。 相似文献