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Precise orbit determination is a major objective in satellite geodesy and data analysis of several satellite missions observing Earth or another planet. Satellite gravity missions such as the Gravity Recovery And Climate Experiment (GRACE) Follow-On mission, require high level of orbit precision (cm level) in order to capture the gravity field modelling of static and time-variable components. The mission’s on-board accelerometers form a key instrument for the direct measurement of non-gravitational perturbations. The accelerometry data processing is crucial for accelerometers with reduced performance following the launch into space such as the case of one of the GRACE-FO satellites. The current study focuses on the GRACE-FO accelerometer calibration modelling within a scheme of precise orbit determination. In particular, the estimation of accelerometer calibration parameters includes bias, drift and scale factors in combination with a minimum number of empirical forces of cycle-per-revolution terms and bias accelerations. The consideration of such empirical perturbations aims at capturing periodic mismodelling effects and accelerometer data errors. The applied approach leads to orbital residuals varying within a few mm to cm while the inter-satellite LRI and KBR range-rate data residuals vary within a few μm/sec.
|Publication date||18 Oct 2022|
|Number of pages||11|
|Publication status||Published - 18 Oct 2022|
|Event||GRACE/GRACE-FO Science Team Meeting 2022 - Potsdam, Germany|
Duration: 18 Oct 2022 → 20 Oct 2022
|Conference||GRACE/GRACE-FO Science Team Meeting 2022|
|Period||18/10/2022 → 20/10/2022|
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GEORB: Gravity and precisE ORBit determination system - GEORB
05/05/2022 → …