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ARTEMIS Lunar Orbit Insertion and Science Orbit Design Through 2013As of late-July 2011, the ARTEMIS mission is transferring two spacecraft from Lissajous orbits around Earth-Moon Lagrange Point #1 into highly-eccentric lunar science orbits. This paper presents the trajectory design for the transfer from Lissajous orbit to lunar orbit insertion, the period reduction maneuvers, and the science orbits through 2013. The design accommodates large perturbations from Earth's gravity and restrictive spacecraft capabilities to enable opportunities for a range of heliophysics and planetary science measurements. The process used to design the highly-eccentric ARTEMIS science orbits is outlined. The approach may inform the design of future planetary moon missions.
Document ID
20150006800
Acquisition Source
Jet Propulsion Laboratory
Document Type
Preprint (Draft being sent to journal)
External Source(s)
Authors
Broschart, Stephen B.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Sweetser, Theodore H.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Angelopoulos, Vassilis
(California Univ. Los Angeles, CA, United States)
Folta, David
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Woodard, Mark
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
April 27, 2015
Publication Date
January 1, 2015
Subject Category
Astrodynamics
Report/Patent Number
AAS 11-509
Meeting Information
Meeting: AAS/AIAA Astrodynamics Specialist Conference
Location: Girdwood, AK
Country: United States
Start Date: July 31, 2011
End Date: August 4, 2011
Sponsors: American Astronautical Society, American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Other
Keywords
lunar orbiters
Time History of Events and Macroscale Interactions during Substorms (THEMIS) mis
Acceleration, Reconnection, Turbulence, and Electrodynamics of the Moons Interac

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