Generating precise and homogeneous orbits for Jason-1 and Jason-2

Flohrer, Claudia; Otten, Michiel; Springer, T.; Dow, J. M.

doi:10.1016/j.asr.2011.02.017

Cited by 30 publications

(10 citation statements)

References 37 publications

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“…For Jason-1 SLR residuals of 1.7 cm (RMS) were reported for 6 months of GPS-only reduced-dynamic orbit determination results in 2002 by Luthcke et al (2003). For comparison, daily mean RMS residuals of 2.0 cm (2002)(2003)(2004)(2005)(2006) to 3.8 cm (2006)(2007)(2008)(2009) were obtained for Jason-1 GPSonly orbit solutions in Flohrer et al (2011), while the corresponding value for Jason-2 amounts to 2.1 cm over the 2008-2009 time frame. -The Gravity field and steady-state Ocean Circulation Explorer (GOCE; Floberghagen et al 2011) mission consisted of a single spacecraft equipped with a high-grade gradiometer for sensing the Earth's gravity field.…”

Section: Slr For Leo Orbit Validationmentioning

confidence: 99%

Satellite laser ranging to low Earth orbiters: orbit and network validation

Arnold

Montenbruck

Hackel

et al. 2018

J Geod

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Satellite laser ranging (SLR) to low Earth orbiters (LEOs) provides optical distance measurements with mm-to cm-level precision. SLR residuals, i.e., differences between measured and modeled ranges, serve as a common figure of merit for the quality assessment of orbits derived by radiometric tracking techniques. We discuss relevant processing standards for the modeling of SLR observations and highlight the importance of line-of-sight dependent range corrections for the various types of laser retroreflector ararys (LRAs). A 1-3 cm consistency of SLR observations and GPSbased precise orbits is demonstrated for a wide range of past and present LEO missions supported by the International Laser Ranging Service (ILRS). A parameter estimation approach is presented to investigate systematic orbit errors and it is shown that SLR validation of LEO satellites is not only able to detect radial but also along-track and cross-track offsets. SLR residual statistics clearly depend on the employed precise orbit determination technique (kinematic vs. reduced-dynamic, float vs. fixed ambiguities) but also reveal pronounced differences in the ILRS station performance. Using the residuals-based parameter estimation approach, corrections to ILRS station coordinates, range bi

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Section: Slr For Leo Orbit Validationmentioning

confidence: 99%

Satellite laser ranging to low Earth orbiters: orbit and network validation

Arnold

Montenbruck

Hackel

et al. 2018

J Geod

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“…Orbit determination using GPS code and carrier phase observations is nowadays a well-proven technique and serves as the primary source of orbit information in numerous geodetic and remote sensing missions in low Earth orbit (Flohrer et al 2011;Bock et al 2014;van den IJssel et al 2015). It likewise forms the basis for the Copernicus POD service (CPOD) which generates precise orbit products for all current Sentinel satellites on an operational basis.…”

Section: Introductionmentioning

confidence: 99%

Precise orbit determination of the Sentinel-3A altimetry satellite using ambiguity-fixed GPS carrier phase observations

Montenbruck

Hackel

Jäggi

2017

J Geod

108

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The Sentinel-3 mission takes routine measurements of sea surface heights and depends crucially on accurate and precise knowledge of the spacecraft. Orbit determination with a targeted uncertainty of less than 2 cm in radial direction is supported through an onboard Global Positioning System (GPS) receiver, a Doppler Orbitography and Radiopositioning Integrated by Satellite instrument, and a complementary laser retroreflector for satellite laser ranging. Within this study, the potential of ambiguity fixing for GPS-only precise orbit determination (POD) of the Sentinel-3 spacecraft is assessed. A refined strategy for carrier phase generation out of low-level measurements is employed to cope with half-cycle ambiguities in the tracking of the Sentinel-3 GPS receiver that have so far inhibited ambiguity-fixed POD solutions. Rather than explicitly fixing doubledifference phase ambiguities with respect to a network of terrestrial reference stations, a single-receiver ambiguity resolution concept is employed that builds on dedicated GPS orbit, clock, and wide-lane bias products provided by the CNES/CLS (Centre National d'Études Spatiales/Collecte Localisation Satellites) analysis center of the International GNSS Service. Compared to float ambiguity solutions, a notably improved precision can be inferred from laser ranging residuals. These decrease from roughly 9 mm down to 5 mm standard deviation for high-grade stations on average over low and high elevations. Furthermore, the ambiguity-fixed orbits offer a substantially improved cross-track accuracy and help to identify lateral offsets in the GPS antenna or center-of-mass (CoM) location. With respect to altimetry, the improved orbit precision also benefits the global consistency of sea surface measurements. However, modeling of the absolute height continues to rely on proper dynamical models for the spacecraft motion as well as ground calibrations for the relative position of the altimeter reference point and the CoM.

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“…The mean values of RMS and mean of the crossover differences for the GFZ VER11, VER6 and selected external orbits derived at Goddard Space Flight Center (GSFC), Centre National d'Etudes Spatiales (CNES), European Space Operations Centre (ESOC) of the European Space Agency (ESA), within REAPER ('Reprocessing of Altimeter Products for ERS') project [32] and available from AVISO CNES data center 2 are given in Table VII. ESOC V.08 orbits were computed using the procedures described by [15] with updates described 2 http://www.aviso.altimetry.fr/en/home.html at ftp://dgn6.esoc.esa.int/envisat/sol8/envisat.sol8.txt. For all TOPEX/Poseidon orbits, altimeter data only from one -TOPEX -altimeter were used.…”

Section: B Orbit Quality Assessment By Single-satellite Crossover Anmentioning

confidence: 99%

Improvements in Precise Orbits of Altimetry Satellites and Their Impact on Mean Sea Level Monitoring

Rudenko

Neumayer

Dettmering

et al. 2017

IEEE Trans. Geosci. Remote Sensing

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Abstract-New, precise, consistent orbits (VER11) of altimetry satellites ERS-1, ERS-2, TOPEX/Poseidon, Envisat, Jason-1 and Jason-2 have been recently derived at GFZ German Research Centre for Geosciences in the extended ITRF2008 terrestrial reference frame using improved models and covering the time span 1991-2015. These orbits show improved quality, as compared to GFZ previous (VER6) orbits derived in 2013. Improved macromodels reduce root mean square (RMS) fits of satellite laser ranging (SLR) observations by 2.6, 6.9 and 7.0% for TOPEX/Poseidon, Jason-1 and Jason-2, respectively. Applying Vienna Mapping Functions 1 instead of Hopfield model for tropospheric correction of Doppler Orbitography and Radiopositioning Integrated by Satellite (DORIS) observations reduces RMS fits of SLR observations by 2.0-2.4% and those of DORIS observations by 2.6% for Envisat and Jason satellites. Using satellite true attitude instead of models improves Jason-1 SLR RMS fits by 41% from July 2012 until July 2013. The VER11 orbits indicate the mean values of the SLR RMS fits between 1.2 and 2.1 cm for the different missions. The internal orbit consistency in the radial direction is between 0.5 and 1.9 cm. The global mean sea level trend for the period 1993 to 2014 from TOPEX, Jason-1 and Jason-2 is increased by 0.2 mm/year to 3.0 mm/year from the GFZ VER6 to VER11 orbits. Regionally, the decadal trends from GFZ VER11 and external orbits vary in the order of 1 mm/year.

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Generating precise and homogeneous orbits for Jason-1 and Jason-2

Cited by 30 publications

References 37 publications

Satellite laser ranging to low Earth orbiters: orbit and network validation

Satellite laser ranging to low Earth orbiters: orbit and network validation

Precise orbit determination of the Sentinel-3A altimetry satellite using ambiguity-fixed GPS carrier phase observations

Improvements in Precise Orbits of Altimetry Satellites and Their Impact on Mean Sea Level Monitoring

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