Heliocentric Escape and Lunar Impact from Near Rectilinear Halo OrbitsSpacecraft departing from the Gateway in a Near Rectilinear Halo Orbit (NRHO) experience gravitational forces from the Moon, the Earth, and the Sun, all of which can be simultaneously significant. These complex dynamics influence the post-separation risk of recontact with the Gateway and the eventual destinations of the departing spacecraft. The current investigation examines the flow of objects leaving NRHOs in the Bicircular Restricted Four-Body Problem, and results are applied to heliocentric escape and lunar impact trajectories in a higher-fidelity ephemeris model. Separation maneuver magnitude, direction, and location are correlated with risk of recontact with the Gateway and successful departure to various destinations.
Document ID
20200001596
Acquisition Source
Johnson Space Center
Document Type
Conference Paper
Authors
Davis, Diane C. (a.i. solutions, Inc. Colorado Springs, CO, United States)
Boudad, Kenza K. (Purdue Univ. West Lafayette, IN, United States)
Power, Rolfe J. (Purdue Univ. West Lafayette, IN, United States)
Howell, Kathleen C. (NASA Headquarters Washington, DC, United States)
Sweeney, Daniel J. (NASA Johnson Space Center Houston, TX, United States)