This paper describes new techniques for use in designing possible trajectories to near-Earth objects (NEOs) given the constraints imposed by the limited propulsive capabilities of small satellites and by being launched as a secondary with larger spacecraft. It illustrates the use of these techniques with the design of a trajectory that achieves rendezvous with the NEO 2007 UN12.
Trajectory design for small-satellite missions to near-earth objects
03.06.2019
Preprint
Keine Angabe
Englisch
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