The Transiting Exoplanet Survey Satellite (TESS) will employ a highly eccentric Earth orbit, in 2:1 lunar resonance, reached with a lunar flyby preceded by 3.5 phasing loops. The TESS mission has limited propellant and several orbit constraints. Based on analysis and simulation, we have designed the phasing loops to reduce delta-V and to mitigate risk due to maneuver execution errors. We have automated the trajectory design process and use distributed processing to generate and to optimize nominal trajectories, check constraint satisfaction, and finally model the effects of maneuver errors to identify trajectories that best meet the mission requirements.
Trajectory Design to Mitigate Risk on the Transiting Exoplanet Survey Satellite (TESS) Mission
AIAA/AAS Astrodynamics Specialist Conference ; 2016 ; Long Beach, CA, United States
2016-09-16
Miscellaneous
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English
TRAJECTORY DESIGN ENHANCEMENTS TO MITIGATE RISK FOR THE TRANSITING EXOPLANET SURVEY SATELLITE (TESS)
British Library Conference Proceedings | 2016
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