Using space manifold dynamics to deploy a small satellite constellation around the Moon

DOI10.1007/s10569-009-9246-xzbMath1223.70089OpenAlexW2080016946WikidataQ123991793 ScholiaQ123991793MaRDI QIDQ642343

Paolo Teofilatto, Mauro Pontani, Ettore Perozzi, Riccardo Marson

Publication date: 26 October 2011

Published in: Celestial Mechanics and Dynamical Astronomy (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.1007/s10569-009-9246-x

zbMATH Keywords

weak stability boundarylow energy transit orbitslunar explorationspace manifold dynamics

Mathematics Subject Classification ID

Celestial mechanics (70F15) Orbital mechanics (70M20)

Related Items (1)

Cylindrical isomorphic mapping applied to invariant manifold dynamics for Earth-Moon missions

Uses Software

• STK

Cites Work

• Earth-Mars halo to halo low thrust manifold transfers
• Low-energy, low-thrust transfers to the Moon
• Dynamical aspects of multi-round horseshoe-shaped homoclinic orbits in the RTBP
• Weak stability boundary trajectories for the deployment of lunar spacecraft constellations
• A note on weak stability boundaries
• Novel spaceways for reaching the Moon: An assessment for exploration
• Artificial halo orbits for low-thrust propulsion spacecraft
• Extension of fast periodic transfer orbits from the Earth-Moon RTBP to the Sun-Earth-Moon quasi-bicircular problem
• A parametric study of stability and resonances around \(L_4\) in the elliptic restricted three-body problem
• A variational proof of existence of transit orbits in the restricted three-body problem
• Connecting orbits and invariant manifolds in the spatial restricted three-body problem
• BURRAU'S PROBLEM OF THREE BODIES
• Low Energy Transit Orbits in the Restricted Three-Body Problems
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