Orbit period modulation for relative motion using continuous low thrust in the two-body and restricted three-body problems

DOI10.1007/S10569-017-9807-3zbMath1447.70020OpenAlexW2770141559WikidataQ102054126 ScholiaQ102054126MaRDI QIDQ1640663

Y. Aharonov

Publication date: 14 June 2018

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

Full work available at URL: https://doi.org/10.1007/s10569-017-9807-3

zbMATH Keywords

restricted three-body problemnon-Keplerian orbitscontinuous low thrustHill-clohessy-wiltshire equationsorbit period modulationrelative spacecraft motion

Mathematics Subject Classification ID

Three-body problems (70F07) Two-body problems (70F05) Orbital mechanics (70M20)

Related Items (1)

Loosely formation-displaced geostationary orbit optimization with complex hybrid sail propulsion

Cites Work

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• On the stability of artificial equilibrium points in the circular restricted three-body problem
• Artificial equilibrium points for a generalized sail in the circular restricted three-body problem
• Nonlinear dynamical analysis for displaced orbits above a planet
• Artificial halo orbits for low-thrust propulsion spacecraft
• The existence and stability of families of displaced two-body orbits
• New approach to halo orbit determination and control

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