Precise Orbit Determination and accelerometry calibration modelling of the GRACE Follow-On mission
Abstract
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) and GRACE Follow-On missions, require high level of orbit precision (cm level) in order to capture the gravity field modelling of static and time-variable components. GRACE satellites are equipped with on-board accelerometers as being a key observation instrument for the direct measurement of non-gravitational perturbations at orbital altitude. The accelerometers calibration modelling within an orbit determination scheme is essential for precise orbits and the gravity field mapping. Furthermore, the accelerometry data processing may become crucial for accelerometers with reduced performance following the launch into space. That is the case of one of the GRACE-FO satellites. The current study’s focus is on the GRACE-FO precise orbit determination along with the accelerometry calibration modelling. In particular, the non-gravitational forces modelling is based on the estimation of accelerometer calibration parameters such as bias, drift and scale factors in combination with empirical forces of cycle-per-revolution terms. The consideration of such empirical perturbations aims at capturing periodic mismodelling effects. The applied approach leads to orbital residuals varying within a few cm while the inter-satellite LRI and KBR range-rate data residuals vary within a few μm/sec.
Info
Conference Poster, 2022
UN SDG Classification
DK Main Research Area
Science/Technology
