Kinematic and reduced-dynamic precise orbit determination of low earth orbiters

Švehla, Dražen; Rothacher, M.

doi:10.5194/adgeo-1-47-2003

Cited by 128 publications

(79 citation statements)

References 6 publications

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“…Inputs to this process include the COSMIC L1 and L2 pseudorange and carrier phase data, precise GPS orbits and transmitter clock offsets from GPS time, LEO attitude information, and earth orientation information. Ionosphere-free phase observations are used in a zero-difference reduced-dynamic filtering approach to estimate the position, velocity, and clock of the LEO (Svehla and Rothacher 2003). In this process, the L1 carrier phase observable in units of meters between receiver r and GPS satellite s is modeled as follows:…”

Section: Leo Precise Orbit Determinationmentioning

confidence: 99%

Quality assessment of COSMIC/FORMOSAT-3 GPS radio occultation data derived from single- and double-difference atmospheric excess phase processing

et al. 2009

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This study evaluates the quality of GPS radio occultation (RO) atmospheric excess phase data derived with single-and double-difference processing algorithms. A spectral analysis of 1 s GPS clock estimates indicates that a sampling interval of 1 s is necessary to adequately remove the GPS clock error with single-difference processing. One week (May 2-8, 2009) of COSMIC/FOR-MOSAT-3 data are analyzed in a post-processed mode with four different processing strategies: (1) double-differencing with 1 s GPS ground data, (2) single-differencing with 30 s GPS clock estimates (standard COSMIC Data Analysis and Archival Center product), (3) single-differencing with 5 s GPS clocks, and (4) single-differencing with 1 s GPS clocks. Analyses of a common set of 5,596 RO profiles show that the neutral atmospheric bending angles and refractivities derived from single-difference processing with 1 s GPS clocks are the highest quality. The random noise of neutral atmospheric bending angles between 60 and 80 km heights is about 1.50e-6 rad for the singledifference cases and 1.74e-6 rad for double-differencing. An analysis of pairs of collocated soundings also shows that bending angles derived from single-differencing with 1 s GPS clocks are more consistent than with the other processing strategies. Additionally, the standard deviation of the differences between RO and high-resolution European Center for Medium range Weather Forecasting (EC-MWF) refractivity profiles at 30 km height is 0.60% for single-differencing with 1 and 5 s GPS clocks, 0.68% for single-differencing with 30 s clocks, and 0.66% for doubledifferencing. A GPS clock-sampling interval of 1 s or less is required for single-and zero-difference processing to achieve the highest quality excess atmospheric phase data for RO applications.

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Section: Leo Precise Orbit Determinationmentioning

confidence: 99%

Quality assessment of COSMIC/FORMOSAT-3 GPS radio occultation data derived from single- and double-difference atmospheric excess phase processing

et al. 2009

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“…The dynamic method and the kinematic method (Š vehla and Rothacher 2003;Jäggi et al 2006Jäggi et al , 2007Hwang et al 2009) are two popular methods for POD of a low-earth orbiter (LEO) using GPS data. These two methods are implemented in the Bernese GPS software version 5.0 (Dach et al 2007).…”

Section: Introductionmentioning

confidence: 99%

Quality assessment of FORMOSAT-3/COSMIC and GRACE GPS observables: analysis of multipath, ionospheric delay and phase residual in orbit determination

et al. 2009

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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,

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“…The mathematical connection between the satellite motion and the gravity field is a key link in the frame of dedicated satellite gravity missions, especially Gravity Recovery and Climate Experiment (GRACE) and Gravity Field and steady-state Ocean Circulation Explorer (GOCE) missions (Tapley et al 2004;ESA 1999;Floberghagen et al 2011), whose measurement principles require a precise orbit determination at the level of a few cm (Förste et al 2008;Pail et al 2011). The space-borne techniques of the two missions have generated extended numerical investigations in the Earth's gravity field modelling as well as into the satellite orbit determination (Xu 2008a;Ilk et al 2008;Svehla and Rothacher 2003;Bobojć and Dro_ zyner 2003;Beutler et al 2010a;Kang et al 2006a, b;Bock et al 2011). …”

Section: Introductionmentioning

confidence: 99%

Assessment of numerical integration methods in the context of low Earth orbits and inter-satellite observation analysis

Papanikolaou

Tsoulis

2016

Acta Geod Geophys

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The integration of differential equations is a fundamental tool in the problem of orbit determination. In the present study, we focus on the accuracy assessment of numerical integrators in what refers to the categories of single-step and multistep methods. The investigation is performed in the frame of current satellite gravity missions i.e. Gravity Recovery and Climate Experiment (GRACE) and Gravity Field and steady-state Ocean Circulation Explorer (GOCE). Precise orbit determination is required at the level of a few cm in order to satisfy the primary missions' scope which is the rigorous modelling of the Earth's gravity field. Therefore, the orbit integration errors are critical for these low earth orbiters. As the result of different schemes of numerical integration is strongly affected by the forces acting on the satellites, various validation tests are performed for their accuracy assessment. The performance of the numerical methods is tested in the analysis of Keplerian orbits as well as in real dynamic orbit determination of GRACE and GOCE satellites by taking into account their sophisticated observation techniques and orbit design. Numerical investigation is performed in a wide range of the fundamental integrators' parameters i.e. the integration step and the order of the multistep methods.

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Kinematic and reduced-dynamic precise orbit determination of low earth orbiters

Cited by 128 publications

References 6 publications

Quality assessment of COSMIC/FORMOSAT-3 GPS radio occultation data derived from single- and double-difference atmospheric excess phase processing

Quality assessment of COSMIC/FORMOSAT-3 GPS radio occultation data derived from single- and double-difference atmospheric excess phase processing

Quality assessment of FORMOSAT-3/COSMIC and GRACE GPS observables: analysis of multipath, ionospheric delay and phase residual in orbit determination

Assessment of numerical integration methods in the context of low Earth orbits and inter-satellite observation analysis

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