Lunar landing trajectory design based on invariant manifold

DOI10.1007/S10483-007-0208-1zbMath1231.37058OpenAlexW2062400492MaRDI QIDQ940210

He-Xi Baoyin, Jun-Feng Li, Sheng-Ping Gong, Yun-Feng Gao

Publication date: 1 September 2008

Published in: Applied Mathematics and Mechanics. (English Edition) (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.1007/s10483-007-0208-1

zbMATH Keywords

three-body probleminvariant manifoldhalo orbitLagrange pointlunar landing trajectory

Mathematics Subject Classification ID

Dynamical systems in control (37N35) Dynamical systems in other branches of physics (quantum mechanics, general relativity, laser physics) (37N20)

Cites Work

• Unnamed Item
• Study of the transfer from the Earth to a halo orbit around the equilibrium point \(L_ 1\)
• The libration points in photogravitational restricted three-body problem
• Heteroclinic connections between periodic orbits in planar restricted circular three-body problem -- a computer-assisted proof
• Connecting orbits and invariant manifolds in the spatial restricted three-body problem
• Low energy transfer to the Moon

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