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Trajectory Design Enhancements to Mitigate Risk for the Transiting Exoplanet Survey Satellite (TESS)The Transiting Exoplanet Survey Satellite (TESS) will employ a highly eccentric Earth orbit, in 2:1 lunar resonance, which will be reached with a lunar flyby preceded by 3.5 phasing loops. The TESS mission has limited propellant and several constraints on the science orbit and on the phasing loops. Based on analysis and simulation, we have designed the phasing loops to reduce delta-V (DV) and to mitigate risk due to maneuver execution errors. We have automated the trajectory design process and use distributed processing to generate and optimal nominal trajectories; to check constraint satisfaction; and finally to model the effects of maneuver errors to identify trajectories that best meet the mission requirements.
Document ID
20160010502
Document Type
Conference Paper
Authors
Dichmann, Donald (NASA Goddard Space Flight Center Greenbelt, MD United States)
Parker, Joel (NASA Goddard Space Flight Center Greenbelt, MD United States)
Nickel, Craig (Applied Defense Solutions, Inc. Fulton, MD, United States)
Lutz, Stephen (Applied Defense Solutions, Inc. Fulton, MD, United States)
Date Acquired
August 22, 2016
Publication Date
September 13, 2016
Subject Category
Astrodynamics
Report/Patent Number
GSFC-E-DAA-TN34561
Meeting Information
AIAA/AAS Astrodynamics Specialist Conference(Long Beach, CA)
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
satellite
trajectory design
Astrodynamics

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