Stationkeeping Analysis for Solar Sailing the L4 Region of Binary Asteroid Systems

Guzzetti, Davide; Sood, Rohan; Chappaz, Loïc; Baoyin, Hexi

doi:10.2514/1.g003994

Cited by 13 publications

(1 citation statement)

References 31 publications

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“…These studies show that the dynamical environment near binary asteroid systems is extremely chaotic, and confirm the results of similar investigations in small-body environments (Ferrari et al, 2016;Tardivel, 2016;Van Wal et al, 2017;Damme et al, 2017;Soldini et al, 2020;Villegas-Pinto et al, 2020). In such low-acceleration environment, the effect of Solar Radiation Pressure (SRP) is extremely relevant and plays a fundamental role in driving the motion of a lightweight spacecraft (Guzzetti et al, 2019;Jean et al, 2019). The goal of the paper is to develop a high-fidelity model of the dynamical environment near Didymos binary and investigate suitable trajectory options to host a CubeSat, with application to Hera's Milani.…”

Section: Introductionsupporting

confidence: 81%

Trajectory Options for Hera’s Milani CubeSat Around (65803) Didymos

Ferrari¹,

Franzese²,

Pugliatti³

et al. 2021

J Astronaut Sci

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The dynamical environment in the close-proximity of small celestial bodies is characterized by a very weak and irregular gravity field. In this lowacceleration deep-space environment, small dynamical perturbations might affect significantly the dynamics of a spacecraft hovering near the surface of such objects. This poses a challenge to the efficient design of trajectories of space probes for space missions aimed at the exploration of small Solar System bodies. This applies especially to CubeSats, small spacecraft with limited autonomy and maneuvering capabilities. In this case, a careful and efficient design of the operational trajectory is mandatory to accomplish the objective of the mission. As a representative and timely case study, we investigate the dynamics around binary asteroid (65803) Didymos, the target of NASA's Double Asteroid Redirection Test (DART) and ESA's Hera missions. We analyze all the relevant dynamical contributions concurring to the acceleration environment near Didymos and provide a subdivision of it into subregions, each identified by a different dynamical regime. With reference to the Hera Milani CubeSat mission scenario, we describe the methodology and design approach to find trajectories in the dayside of Didymos system. Finally, we provide examples of suitable trajectory options to host the operational phase of the Hera Milani CubeSat.

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Section: Introductionsupporting

confidence: 81%

Trajectory Options for Hera’s Milani CubeSat Around (65803) Didymos

Ferrari¹,

Franzese²,

Pugliatti³

et al. 2021

J Astronaut Sci

View full text Add to dashboard Cite

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Floquet modes and stability analysis of periodic orbit-attitude solutions along Earth–Moon halo orbits

Colombi

Colagrossi

Lavagna

2021

Celest Mech Dyn Astr

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Future space programmes pose some interesting research problems in the field of non-Keplerian dynamics, being the Moon and the cislunar space central in the proposed roadmap for the future space exploration. In these regards, the deployment of a cislunar space station on a non-Keplerian orbit in the lunar vicinity is a fundamental milestone to be achieved. The paper investigates the natural orbit-attitude dynamics and the attitude stabilisation of coupled motions for extended bodies in the Earth–Moon system. The discussion is carried out analysing the phase space of natural dynamics, constituted by both the orbital and the rotational periodic motions of a spacecraft in cislunar orbits. Floquet theory is applied to periodic orbit-attitude solutions in lunar proximity, to characterise their attitude stability properties and their attitude manifolds, which are discussed and analysed focusing on their dynamical features applicable to cislunar environment. Attitude stabilisation methods are proposed and developed, with particular attention to spin-stabilised solutions. Periodic orbit-attitude dynamics are studied to highlight possible favourable conditions that may be exploited to host a cislunar space station with a simplified control action. The focus of the analysis is dedicated to halo orbits and near-rectilinear halo orbit in the circular restricted three-body problem Earth–Moon system.

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