Combined low-thrust propulsion and invariant manifold trajectories to capture NEOs in the Sun-Earth circular restricted three-body problem

DOI10.1007/s10569-014-9589-9zbMath1409.70007OpenAlexW1984261621MaRDI QIDQ5962793

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Publication date: 24 February 2016

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

Full work available at URL: https://doi.org/10.1007/s10569-014-9589-9

zbMATH Keywords

invariant manifoldsoptimal control problemasteroid retrieval candidatesdistant prograde periodic orbit (DPO)easily retrievable objects (EROs)libration point periodic orbit (LPO)low-thrust propulsionnear-Earth object capturespecial dedicated sets

Mathematics Subject Classification ID

Celestial mechanics (70F15) Orbital mechanics (70M20) Invariant manifolds for ordinary differential equations (34C45) (n)-body problems (70F10)

Related Items (1)

Direct and indirect capture of near-Earth asteroids in the Earth-Moon system

Uses Software

• OTIS

Cites Work

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