Publications related to the GRACE Missions (no abstracts)

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Impact of Deployable Solar Panels on Gravity Field Recovery in GRACE-like Satellites: a Closed-Loop Simulation Study

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.

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@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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