Trajectory refinement of three-body orbits in the real solar system model

Tos, Diogene Alessandro Dei; Topputo, Francesco

doi:10.1016/j.asr.2017.01.039

Cited by 34 publications

(19 citation statements)

References 20 publications

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“…The target orbit is a Halo at the L2 point of the Earth-Moon system, with a period of about half a synodic period. The mission has an expected mission lifetime of 1 year [15,16], starting from the 21 March 2024 epoch to 21 March 2025. The trajectory is plotted in Fig.…”

Section: Lumio Trajectorymentioning

confidence: 99%

Feasibility analysis of GNSS-based navigation for LUMIO mission

Bernelli‐Zazzera

Forte

2022

CEAS Space J

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The paper presents the design of a realistic model of the GNSS constellations GPS and Galileo to perform a navigation performances analysis in lunar environment. Starting from the visibility analysis, the link-budget of each visible GNSS spacecraft is estimated using for each one realistic data for the transmitted power and environmental and system parameters. The navigation performances are evaluated in this scenario. The model implemented is applied to the trajectory of the LUMIO CubeSat mission and the results are commented. LUMIO is a lunar CubeSat mission, on a Halo orbit at the L2 point of the Earth–Moon system, designed to observe the measured meteoroid impacts on the far side of the Moon. LUMIO has been designed to perform autonomous onboard navigation with an accuracy better than 30 km for more than 99.7% of the time. The navigation analysis in this work can be compared to such a requirement to evaluate if a GNSS-based navigation solution could be employed as well.

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Section: Lumio Trajectorymentioning

confidence: 99%

Feasibility analysis of GNSS-based navigation for LUMIO mission

Bernelli‐Zazzera

Forte

2022

CEAS Space J

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“…Although quasi-halos, shown in Fig. 12, are computed for a fixed initial epoch, the persistence of libration point orbits in the solar system ephemeris model allows wide freedom in the refinement algorithm, which also includes the mission starting at different epochs [11].…”

Section: Orbitmentioning

confidence: 99%

LUMIO: An Autonomous CubeSat for Lunar Exploration

Speretta

Cervone

Sundaramoorthy

et al. 2019

Space Operations: Inspiring Humankind's Future

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The Lunar Meteoroid Impact Observer (LUMIO) is one of the four projects selected within ESA's SysNova competition to develop a small satellite for scientific and technology demonstration purposes to be deployed by a mothership around the Moon. The mission utilizes a 12U form-factor CubeSat which carries the LUMIO-Cam, an optical instrument capable of detecting light flashes in the visible spectrum to continuously monitor and process the meteoroids impacts. In this chapter, we will describe the mission concept and focus on the performance of a novel navigation concept using Moon images taken as byproduct of the LUMIO-Cam operations. This new approach will considerably limit the operations burden on ground, aiming at autonomous orbit-attitude navigation and control. Furthermore, an efficient and autonomous strategy for collection, processing, categorization, and storage of payload data is also described to cope with the limited contact time and downlink bandwidth. Since all communications have to go via a lunar orbiter, all commands and telemetry/data will have to be forwarded to/from the mothership. This will prevent quasi-real-time operations and will be the first time for CubeSats

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“…All orbits are computed starting from 2020 August 30 00:00:00.00 TDB. Although quasi-halos, shown in Figure 4, are computed for a fixed initial epoch, the persistence of libration point orbits in the solar system ephemeris model allows wide freedom in the refinement algorithm, which also includes mission starting at different epochs [12].…”

Section: Orbitmentioning

confidence: 99%

LUMIO: achieving autonomous operations for Lunar exploration with a CubeSat

Speretta

Topputo

Biggs

et al. 2018

2018 SpaceOps Conference

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The Lunar Meteoroid Impacts Observer (LUMIO) is one of the four projects selected within ESA's SysNova competition to develop a small satellite for scientific and technology demonstration purposes to be deployed by a mother ship around the Moon. The mission utilizes a 12U form-factor CubeSat which carries the LUMIO-Cam, an optical instrument capable of detecting light flashes in the visible spectrum to continuously monitor and process the meteoroids impacts. In this paper, we will describe the mission concept and focus on the performance of a novel navigation concept using Moon images taken as byproduct of the LUMIO-Cam operations. This new approach will considerably limit the operations burden on ground, aiming at autonomous orbit-attitude navigation and control. Furthermore, an efficient and autonomous strategy for collection, processing, categorization, and storage of

show abstract

Trajectory refinement of three-body orbits in the real solar system model

Cited by 34 publications

References 20 publications

Feasibility analysis of GNSS-based navigation for LUMIO mission

Feasibility analysis of GNSS-based navigation for LUMIO mission

LUMIO: An Autonomous CubeSat for Lunar Exploration

LUMIO: achieving autonomous operations for Lunar exploration with a CubeSat

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