Mon Oct 13, F. Flechtner
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Leipner, Andreas, Kupriyanov, Alexey, Reis, Arthur, Knabe, Annike, Schilling, Manuel, Müller, Vitali, Weigelt, Matthias, Müller, Jürgen, and List, Meike, 2025. Impact of Deployable Solar Panels on Gravity Field Recovery in GRACE-like Satellites: a Closed-Loop Simulation Study. Journal of Geodesy, 99(7):59, doi:10.1007/s00190-025-01983-1.
• from the NASA Astrophysics Data System • by the DOI System •
@ARTICLE{2025JGeod..99...59L,
author = {{Leipner}, Andreas and {Kupriyanov}, Alexey and {Reis}, Arthur and {Knabe}, Annike and {Schilling}, Manuel and {M{\"u}ller}, Vitali and {Weigelt}, Matthias and {M{\"u}ller}, J{\"u}rgen and {List}, Meike},
title = "{Impact of Deployable Solar Panels on Gravity Field Recovery in GRACE-like Satellites: a Closed-Loop Simulation Study}",
journal = {Journal of Geodesy},
keywords = {Future satellite gravimetry missions, Finite element modeling, Satellite shapes, Optical accelerometry, Gravity field recovery, Closed-loop simulation},
year = 2025,
month = jul,
volume = {99},
number = {7},
eid = {59},
pages = {59},
abstract = "{Future satellite gravimetry missions must meet increasing scientific
demands, requiring advanced technologies, e.g., novel inertial
sensors, laser ranging systems and potentially electric
thrusters to operate in a drag-free regime. Deployable solar
panels offer a promising solution by providing sufficient power
even under unfavorable illumination conditions, without
significantly increasing satellite dimensions or mass. This
study evaluates the impact of single and double deployable solar
panels on gravity field recovery (GFR) through closed-loop
simulations. Five GRACE-like satellite configurations were
analyzed, each with distinct finite element models and inertia
properties. Detailed orbit simulations included non-spherical
static gravity field and impacting non-gravitational force
models. Satellites drag coefficients varied from 2.25 to 4.5,
depending on configuration. GFR was assessed using degree RMS of
spherical harmonic coefficient differences between the recovered
and reference fields. GFR results show that discrepancies
between the modified and standard configurations are mainly
driven by variations of the actuation noise of the modeled
optical accelerometer - simplified gravitational reference
sensor (SGRS). SGRS performance, in turn, depends on the
satellite's cross-sectional area. Moreover, the convergence of
residuals in the spectral domain for simulated orbits with
different drag coefficients confirmed the dominant role of SGRS
performance in the retrieved gravity field.}",
doi = {10.1007/s00190-025-01983-1},
adsurl = {https://ui.adsabs.harvard.edu/abs/2025JGeod..99...59L},
adsnote = {Provided by the SAO/NASA Astrophysics Data System}
}
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