Abstract
This paper discusses the applications of Distant Retrograde Orbits (DROs) about the Moon in support of advanced concepts such as NASA’s Asteroid Redirect Mission. It studies how to build a direct transfer from a low Earth orbit to a DRO, paying attention to the navigation challenges of each transfer option. The characteristics of planar DROs in the Earth-Moon system are examined. The paper focuses on a DRO that is in a 2:1 resonance with the lunar synodic period. Trade studies illustrate the relationships between the transfer trajectory duration, required launch energy, and DRO orbit insertion Δv cost. In addition, powered lunar flyby transfers are explored to determine potential cost savings in Δv. These investigations are conducted in both the Circular Restricted Three-Body system and in a high-fidelity model of the solar system.
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