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Artemis I Trajectory Design and OptimizationThis paper presents the overall trajectory design and optimization process for NASA’s Artemis I mission to send an uncrewed Orion vehicle to a lunar Distant Retrograde Orbit (DRO). The on-orbit trajectory begins at the Space Launch System (SLS) core separation and ends at the Orion service module Earth Entry Interface (EI) point. The details of the trajectory optimization process are presented, including design of nominal and extended mission options, launch windows, and abort options. Novel design techniques are also discussed to account for contingencies, such as using auxiliary thrusters to protect against main engine failure and applying trajectory shaping to mitigate or reduce eclipse durations.
Document ID
20205005150
Acquisition Source
Johnson Space Center
Document Type
Conference Paper
Authors
Amelia L Batcha
(Johnson Space Center Houston, Texas, United States)
Jacob Williams
(Johnson Space Center Houston, Texas, United States)
Timothy F Dawn
(Johnson Space Center Houston, Texas, United States)
Jeffrey P Gutkowski
(Johnson Space Center Houston, Texas, United States)
Maxon V Widner
(Jacobs (United States) Dallas, Texas, United States)
Sarah L Smallwood
(Johnson Space Center Houston, Texas, United States)
Brian J Killeen
(Johnson Space Center Houston, Texas, United States)
Elizabeth C Williams
(Jacobs (United States) Dallas, Texas, United States)
Robert E Harpold
(Jacobs (United States) Dallas, Texas, United States)
Date Acquired
July 27, 2020
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AAS 20-649
Meeting Information
Meeting: 2020 AAS/AIAA Astrodynamics Specialist Conference
Location: Virtual
Country: US
Start Date: August 9, 2020
End Date: August 12, 2020
Sponsors: American Astronomical Society
Funding Number(s)
WBS: 573754.01.01.01.50.02
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
Artemis I
trajectory optimization
Orion
trajectory design
mission analysis
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