Impact of accelerometer modeling and parametrization on the BepiColombo orbit determination and gravimetry experiment

verfasst von: Alireza HosseiniArani, Nicolas Thomas, Adrian Jäggi, Daniel Arnold, Stefano Bertone
Abstract: Italian Spring Accelerometer (ISA, Iafolla and Nazolli, 2001) is one of the instruments on-board Mercury Planetary Orbiter (MPO), one of the two spacecraft of the European Space Agency's (ESA) BepiColombo mission (Benkhoff et al., 2010). It will arrive at Mercury by the end of 2025. The scientific objectives of ISA are mostly related to . Together with the Mercury orbiter Radio-Science Experiment (MORE, Milani et al., 2001), ISA will provide information on the spacecraft orbit, on Mercury's gravity field, and hence on its interior structure. The goal of this work is to study the influence of the accelerometer modelling and of its parameterization on the accuracy of orbit reconstruction (OD) and on the gravimetry experiment. We propagate the orbit of MPO using a realistic force model, including gravitational and non-gravitational forces. We simulate 2-way X band Doppler observations affected by a white noise consistent with previous studies. Based on the propagated orbits, we also simulate accelerometer measurements by ISA using the accelerometer model presented by Alessi et al. (2012) and Cical`o et al. (2016). We use the Bernese software (BSW) to perform the simulation and OD. This software has been extensively used for Precise Orbit Determination of Earth orbiting spacecraft using GNSS data collected by on-board receivers and for subsequent determination of the Earth gravity field. Its planetary extension has recently also been used in Lunar geodesy (GRAIL, Arnold et al, 2015; Bertone et al, 2020) and for mission studies inI the outer Solar System (Desprats et al, 2020). The OD and the recovery of the gravity field are performed in a "closed loop simulation". We use the MESSENGER-derived gravity field solution HGM050 d/o 50 in the simulation phase and suitably perturb or truncate it at the stage of orbit reconstruction. We reconstruct the orbit based on the simulated Doppler, perturbed initial condition, a reduced force model, and by replacing the non-gravitational forces by simulated accelerometer measurements (i.e., affected by colored noise). We perform a combined recovery of orbit, accelerometer parameters and Mercury gravitational field Finally, we discuss the achievable accuracy in determining the accelerometer bias and scaling factors and their impact on the OD and gravimetry experiment....
Organisationseinheit(en): Institut für Erdmessung
QUEST Leibniz Forschungsschule
Institut für Theoretische Physik
Institut für Fertigungstechnik und Werkzeugmaschinen
Typ: Abstract
Publikationsdatum: 01.2021
Publikationsstatus: Veröffentlicht
: Details im Forschungsportal „Research@Leibniz University“

BibTeX

@conference{73b8e8f54d564e659062dbf358afe71d,
title = "Impact of accelerometer modeling and parametrization on the BepiColombo orbit determination and gravimetry experiment",
abstract = "Italian Spring Accelerometer (ISA, Iafolla and Nazolli, 2001) is one of the instruments on-board Mercury Planetary Orbiter (MPO), one of the two spacecraft of the European Space Agency's (ESA) BepiColombo mission (Benkhoff et al., 2010). It will arrive at Mercury by the end of 2025. The scientific objectives of ISA are mostly related to . Together with the Mercury orbiter Radio-Science Experiment (MORE, Milani et al., 2001), ISA will provide information on the spacecraft orbit, on Mercury's gravity field, and hence on its interior structure. The goal of this work is to study the influence of the accelerometer modelling and of its parameterization on the accuracy of orbit reconstruction (OD) and on the gravimetry experiment. We propagate the orbit of MPO using a realistic force model, including gravitational and non-gravitational forces. We simulate 2-way X band Doppler observations affected by a white noise consistent with previous studies. Based on the propagated orbits, we also simulate accelerometer measurements by ISA using the accelerometer model presented by Alessi et al. (2012) and Cical`o et al. (2016). We use the Bernese software (BSW) to perform the simulation and OD. This software has been extensively used for Precise Orbit Determination of Earth orbiting spacecraft using GNSS data collected by on-board receivers and for subsequent determination of the Earth gravity field. Its planetary extension has recently also been used in Lunar geodesy (GRAIL, Arnold et al, 2015; Bertone et al, 2020) and for mission studies inI the outer Solar System (Desprats et al, 2020). The OD and the recovery of the gravity field are performed in a {"}closed loop simulation{"}. We use the MESSENGER-derived gravity field solution HGM050 d/o 50 in the simulation phase and suitably perturb or truncate it at the stage of orbit reconstruction. We reconstruct the orbit based on the simulated Doppler, perturbed initial condition, a reduced force model, and by replacing the non-gravitational forces by simulated accelerometer measurements (i.e., affected by colored noise). We perform a combined recovery of orbit, accelerometer parameters and Mercury gravitational field Finally, we discuss the achievable accuracy in determining the accelerometer bias and scaling factors and their impact on the OD and gravimetry experiment....",
author = "Alireza HosseiniArani and Nicolas Thomas and Adrian J{\"a}ggi and Daniel Arnold and Stefano Bertone",
year = "2021",
month = jan,
language = "Undefined/Unknown",
}