Invariant relative orbits for spacecraft formation flying in high-order gravitational field

Ma, Yuechen; He, Yongfeng; Xu, Ming; Zhou, Qingrui; Chen, Xi

doi:10.1016/j.actaastro.2021.08.027

Cited by 3 publications

(1 citation statement)

References 36 publications

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“…He, Armellin, and Xu developed a model to design bounded relative orbits in the full zonal problem, therefore including the J n terms up to the desired degree, based on the Taylor approximation of Poincaré maps and numerical refinement [19]. Ma et al examined the same problem to determine invariant relative orbits (negligible drift and variation in the amplitude of the oscillations) using double-averaged Delaunay orbital elements [20].…”

Section: Introductionmentioning

confidence: 99%

Dynamics and Control of Satellite Formations Invariant under the Zonal Harmonic Perturbation

Carletta

2023

Applied Sciences

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A satellite formation operating in low-altitude orbits is subject to perturbations associated to the higher-order harmonics of the gravitational field, which cause a degradation of the formation configurations designed based on the unperturbed model of the Hill–Clohessy–Wiltshire equations. To compensate for these effects, periodic reconfiguration maneuvers are necessary, requiring the prior allocation of a propellant mass budget and, eventually, the use of resources from the ground segment, having a non-negligible impact on the complexity and cost of the mission. Using the Hamiltonian formalism and canonical transformations, a model is developed that allows designing configurations for formation flying invariant with respect to the zonal harmonic perturbation. Jn invariant configurations can be characterized, selecting the drift rate (or boundedness condition) and the amplitude of the oscillations, based on four parameters which can be easily converted in position and velocity components for the satellites of the formation. From this model, a guidance strategy is developed to inject a satellite approaching another spacecraft into a bounded relative trajectory about it and the optimal time for the maneuver, minimizing the total ΔV, is identified. The effectiveness of the model and of the guidance strategy is verified on some scenarios of interest for formations operating in a sun-synchronous and a medium-inclination low Earth orbit and a medium-inclination lunar orbit.

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Section: Introductionmentioning

confidence: 99%

Dynamics and Control of Satellite Formations Invariant under the Zonal Harmonic Perturbation

Carletta

2023

Applied Sciences

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Naturally bounded relative motion for formation flying near triangular libration points

Sun

et al. 2023

Advances in Space Research

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Non-Singular Fast Terminal Sliding Mode Control with Super-Twisting ESO for Spacecraft Formation Flying Systems

Li,

Tang,

Zhong

et al. 2023

2023 China Automation Congress (CAC)

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Invariant relative orbits for spacecraft formation flying in high-order gravitational field

Cited by 3 publications

References 36 publications

Dynamics and Control of Satellite Formations Invariant under the Zonal Harmonic Perturbation

Dynamics and Control of Satellite Formations Invariant under the Zonal Harmonic Perturbation

Naturally bounded relative motion for formation flying near triangular libration points

Non-Singular Fast Terminal Sliding Mode Control with Super-Twisting ESO for Spacecraft Formation Flying Systems

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