Optimal low-thrust transfers between libration point orbits

Details Optimal low-thrust transfers between libration point orbits Optimal low-thrust transfers between libration point orbits

Jan 2012

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2012cemda.112....1r&link_type=abstract

Celestial Mechanics and Dynamical Astronomy, Volume 112, Issue 1, pp.1-21

Astronomy and Astrophysics

Astronomy

Circular Restricted Three-Body Problem, Bicircular Four-Body Model, Low-Thrust, Invariant Tori, Invariant Manifold, Continuation Procedure

Scientific paper

Over the past three decades, ballistic and impulsive trajectories between libration point orbits (LPOs) in the Sun-Earth-Moon system have been investigated to a large extent. It is known that coupling invariant manifolds of LPOs of two different circular restricted three-body problems (i.e., the Sun-Earth and the Earth-Moon systems) can lead to significant mass savings in specific transfers, such as from a low Earth orbit to the Moon's vicinity. Previous investigations on this issue mainly considered the use of impulsive maneuvers along the trajectory. Here we investigate the dynamical effects of replacing impulsive Δ V's with low-thrust trajectory arcs to connect LPOs using invariant manifold dynamics. Our investigation shows that the use of low-thrust propulsion in a particular phase of the transfer and the adoption of a more realistic Sun-Earth-Moon four-body model can provide better and more propellant-efficient solution. For this purpose, methods have been developed to compute the invariant tori and their manifolds in this dynamical model.

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