Optimizing low-thrust and gravity assist maneuvers to design interplanetary trajectories

Details Optimizing low-thrust and gravity assist maneuvers to design interplanetary trajectories Optimizing low-thrust and gravity assist maneuvers to design interplanetary trajectories

2011-05-10

arxiv.org/abs/1105.1829v1

The Journal of the astronautical sciences 2003, vol. 51, no1, pp. 13-35

Mathematics

Optimization and Control

Scientific paper

In this paper a direct method based on a transcription by finite elements in time has been used to design optimal interplanetary trajectories, exploiting a combination of gravity assist maneuvers and low-thrust propulsion. A multiphase parametric approach has been used to introduce swing-bys, treated as coast phases between two thrusted or coasting trajectory arcs. Gravity maneuvers are at first modeled with a linked-conic approximation and then introduced through a full three-dimensional propagation including perturbations by the Sun. The method is successfully applied to the design of a mission to planet Mercury, for which different options corresponding to different sequences of gravity maneuvers or launch opportunities are presented.

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