This thesis regards two main topics: the modelling of the Galilean satellites dynamics and the simulations of orbit determination experiments of the JUICE space mission. In the first part, I developed a semi-analytical secular model of the Galilean satellites' dynamics. This model reproduces well the resonant and secular features of all the orbital elements of the moons and it describes their orbital evolution due to the tidal dissipation acting in the system. Moreover, it is suitable for very long propagations of the satellites motion and studies about their migration. In the second part, I simulated the data (radioscience and VLBI) that the future ESA mission JUICE will provide when it will arrive in the Jovian system, in order to perform orbit determination experiments. In particular, I focussed my work on the estimation of the dissipative parameters of the system and I investigated the chaotic effects on the orbit of the spacecraft due to the multiple flybys phase of the mission.
The Galilean satellites dynamics and the estimation of the Jovian system?s dissipation from JUICE data
2019
Abstract
This thesis regards two main topics: the modelling of the Galilean satellites dynamics and the simulations of orbit determination experiments of the JUICE space mission. In the first part, I developed a semi-analytical secular model of the Galilean satellites' dynamics. This model reproduces well the resonant and secular features of all the orbital elements of the moons and it describes their orbital evolution due to the tidal dissipation acting in the system. Moreover, it is suitable for very long propagations of the satellites motion and studies about their migration. In the second part, I simulated the data (radioscience and VLBI) that the future ESA mission JUICE will provide when it will arrive in the Jovian system, in order to perform orbit determination experiments. In particular, I focussed my work on the estimation of the dissipative parameters of the system and I investigated the chaotic effects on the orbit of the spacecraft due to the multiple flybys phase of the mission.File | Dimensione | Formato | |
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https://hdl.handle.net/20.500.14242/148153
URN:NBN:IT:UNIPI-148153