CHAMP and GRACE accelerometer calibration by GPS-based orbit determination

Helleputte, Tom van; Doornbos, Eelco; Visser, Pieter

doi:10.1016/j.asr.2009.02.017

Cited by 54 publications

(39 citation statements)

References 24 publications

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“…The Y SBF (cross-track) calibration for the CHAMP and GRACE satellites using GPS data is problematic, 29 because of the relatively low acceleration signal, and because of the limited capability of accelerations in this direction to perturb the orbit, compared to along-track accelerations. Both limitations are the result of fundamental orbital dynamics in combination with the tight attitude control of the spacecraft, as discussed at the start of Section III.A.…”

Section: Algorithm Tests Iva Error Assessment Using Simulated Amentioning

confidence: 99%

Neutral Density and Crosswind Determination from Arbitrarily Oriented Multiaxis Accelerometers on Satellites

Doornbos¹,

IJssel²,

Lühr³

et al. 2010

Journal of Spacecraft and Rockets

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166

198

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Originally published as:Doornbos, E., van den Ijssel, J., Lühr, H., Förster, M., Koppenwallner, G. (2010): Neutral density and crosswind determination from arbitrarily oriented multi-axis accelerometers on satellites. adjacent days where the satellite was in its nominal attitude mode. These investigations result in recommendations for the design of future satellite accelerometer missions for thermosphere research.

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Section: Algorithm Tests Iva Error Assessment Using Simulated Amentioning

confidence: 99%

Neutral Density and Crosswind Determination from Arbitrarily Oriented Multiaxis Accelerometers on Satellites

Doornbos¹,

IJssel²,

Lühr³

et al. 2010

Journal of Spacecraft and Rockets

Self Cite

166

198

View full text Add to dashboard Cite

show abstract

“…The calibration of the in-track accelerometer axis was performed by solving for daily accelerometer biases using independent GPS satellite-to-satellite tracking data (VanHelleputte et al, 2009). This procedure was performed for data from 5 May 2001 onwards.…”

Section: Champ Orbits and Datamentioning

confidence: 99%

Substorm-related thermospheric density and wind disturbances derived from CHAMP observations

2010

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Abstract. The input of energy and momentum from the magnetosphere is most efficiently coupled into the high latitude ionosphere-thermosphere. The phenomenon we are focusing on here is the magnetospheric substorm. This paper presents substorm related observations of the thermosphere derived from the CHAMP satellite. With its sensitive accelerometer the satellite can measure the air density and zonal winds. Based on a large number of substorm events the average high and low latitude thermospheric response to substorm onsets was deduced. During magnetic substorms the thermospheric density is enhanced first at high latitudes. Then the disturbance travels at an average speed of 650 m/s to lower latitudes, and 3-4 h later the bulge reaches the equator on the night side. Under the influence of the Coriolis force the travelling atmospheric disturbance (TAD) is deflected westward. In accordance with present-day atmospheric models the disturbance zonal wind velocities during substorms are close to zero near the equator before midnight and attain moderate westward velocities after midnight. In general, the wind system is only weakly perturbed ( v y < 20 m/s) by substorms.

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“…The detailed GRACE and GOCE data processing which is implemented here follows the standard procedures that are documented in the relevant literature (Papanikolaou and Tsoulis 2014;Papanikolaou 2012). For the case of GRACE, it incorporates the corrections to the initial KBR observations (Case et al 2010) as well as the use of precise calibration parameters for the accelerometers provided by the TU Delft thermosphere web server thermosphere.tudelft.nl Helleputte et al 2009). For the case of GOCE, one cycle per revolution (1-CPR) empirical parameters have been included in the orbit estimation algorithm according to the following equation for each coordinate direction…”

Section: Goce and Grace Orbit Analysismentioning

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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CHAMP and GRACE accelerometer calibration by GPS-based orbit determination

Cited by 54 publications

References 24 publications

Neutral Density and Crosswind Determination from Arbitrarily Oriented Multiaxis Accelerometers on Satellites

Neutral Density and Crosswind Determination from Arbitrarily Oriented Multiaxis Accelerometers on Satellites

Substorm-related thermospheric density and wind disturbances derived from CHAMP observations

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

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