On the advantages of exploiting the hierarchical structure of astrodynamical models

Tos, Diogene Alessandro Dei; Topputo, Francesco

doi:10.1016/j.actaastro.2017.02.025

Cited by 17 publications

(13 citation statements)

References 23 publications

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“…Comparatively, the SP is reached more often when departing from smaller halos. Also, there are less multiple SP passage for increasing out-of-plane amplitude; see plots of A z vs other parameters and histograms in position (6,6).…”

Section: Exploration In the Sun-earth-moon Rfbpmentioning

confidence: 99%

“…Orbits are sought in the Circular Restricted Three-Body Problem (CRTBP) with Sun and Earth as primaries, in the bicircular Restricted Four-Body Problem (RFBP) that includes the Moon, as well as in a full-ephemeris, three-dimensional restricted n-body model stated in a roto-pulsating frame incorporating non-gravitational forces [7], termed Roto-Pulsating Restricted n-Body Problem (RPRnBP). This design strategy follows the hierarchy of astrodynamical models presented in [6]. A large scale survey is completed encompassing more than 200, 000 initial conditions on several L 1,2 libration point orbits.…”

Section: Introductionmentioning

confidence: 99%

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The Sun–Earth saddle point: characterization and opportunities to test general relativity

Topputo

Tos

Rasotto³

et al. 2018

Celest Mech Dyn Astr

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The saddle points are locations where the net gravitational accelerations balance. These regions are gathering more attention within the astrophysics community. Regions about the saddle points present clean, close-to-zero background acceleration environments where possible deviations from General Relativity can be tested and quantified. Their location suggests that flying through a saddle point can be accomplished by leveraging highly nonlinear orbits.In this paper, the geometrical and dynamical properties of the Sun-Earth saddle point are characterized. A systematic approach is devised to find ballistic orbits that experience one or multiple passages through this point. A parametric analysis is performed to consider spacecraft initially on L 1,2 Lagrange point orbits. Sun-Earth saddle point ballistic fly-through trajectories are evaluated and classified for potential use. Results indicate an abundance of short-duration, regular solutions with a variety of characteristics.

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Section: Exploration In the Sun-earth-moon Rfbpmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

The Sun–Earth saddle point: characterization and opportunities to test general relativity

Topputo

Tos

Rasotto³

et al. 2018

Celest Mech Dyn Astr

Self Cite

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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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“…An exhaustive description of the orbit design for LUMIO can be found in [9]. A set of quasi-periodic halo orbits about Earth-Moon L 2 are found by employing the methodology described in [10]. Fourteen quasi-halo orbits are computed in the high-fidelity roto-pulsating restricted n-body problem and saved as SPICE kernels.…”

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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On the advantages of exploiting the hierarchical structure of astrodynamical models

Cited by 17 publications

References 23 publications

The Sun–Earth saddle point: characterization and opportunities to test general relativity

The Sun–Earth saddle point: characterization and opportunities to test general relativity

Feasibility analysis of GNSS-based navigation for LUMIO mission

LUMIO: An Autonomous CubeSat for Lunar Exploration

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