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Design and Implementation of the ARTEMIS Lunar Transfer Using Multi-Body DynamicsThe use of multi-body dynamics to design the transfer of spacecraft from Earth elliptical orbits to the Earth-Moon libration (L(sub 1) and L(sub 2)) orbits has been successfully demonstrated by the Acceleration Reconnection and Turbulence and Electrodynamics of the Moon's Interaction with the Sun (ARTEMIS) mission. Operational support of the two ARTEMIS spacecraft is a final step in the realization of a design process that can be used to transfer spacecraft with restrictive operational constraints and fuel limitations. The focus of this paper is to describe in detail the processes and implementation of this successful approach.
Document ID
20180001202
Acquisition Source
Goddard Space Flight Center
Document Type
Conference Paper
Authors
Folta, David (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Woodard, Mark (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Sweetser, Theodore (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Broschart, Stephen B. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Cosgrove, Daniel (California Univ. Berkeley, CA, United States)
Date Acquired
February 15, 2018
Publication Date
July 31, 2011
Subject Category
Astrodynamics
Spacecraft Design, Testing And Performance
Report/Patent Number
AAS 11-511
LEGNEW-OLDGSFC-GSFC-LN-1222
Meeting Information
Meeting: American Astronautical Society/American Institute of Aeronautics and Astronautics (AAS/AIAA) Astrodynamics Specialist Conference
Location: Girdwood, AK
Country: United States
Start Date: July 31, 2011
End Date: August 4, 2011
Sponsors: American Inst. of Aeronautics and Astronautics, American Astronautical Society
Distribution Limits
Public
Copyright
Public Use Permitted.

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