A Pattern Search Method to Optimize Mars Exploration Trajectories

The Korean National Space Council recently released “Mars Exploration 2045” as part of its future strategic plan. The operations for a Mars explorer can be defined based on domestically available capabilities, such as ground operations, launch, in-space transport and deep space link. Accordingly, al...

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Bibliographic Details
Published in:Aerospace 2023-10, Vol.10 (10), p.827
Main Authors: Choi, Su-Jin, Kang, Hongjae, Lee, Keejoo, Kwon, Sejin
Format: Article
Language:English
Subjects:
15-day launch period
Antennas
Antennas (Electronics)
Artificial intelligence
Discovery and exploration
eco-friendly propulsion system
Energy consumption
Ground operations
Infrastructure
Mars
Mars (Planet)
Mars exploration
Mars orbiters
Methods
Objective function
optimal trajectory design
Optimization
Orbit insertion
Pattern search
pattern search method
Propulsion systems
Search methods
Space exploration
Strategic planning (Business)
Trajectory optimization
Vehicles
velocity increment (∆V)
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Summary:The Korean National Space Council recently released “Mars Exploration 2045” as part of its future strategic plan. The operations for a Mars explorer can be defined based on domestically available capabilities, such as ground operations, launch, in-space transport and deep space link. Accordingly, all of our exploration scenarios start from the Naro space center, and the pathway to Mars is optimized using an objective function that minimizes the required ∆V. In addition, the entire phase of Mars orbit insertion should remain in contact with our deep space antennas, a measure that is imposed as an operational constraint. In this study, a pattern search method is adopted, as it can handle a nonlinear problem without relying on the derivatives of the objective function, and optimal trajectories are generated on a daily basis for a 15-day launch period. The robustness of this direct search method is confirmed by consistently converged solutions showing, in particular, that the ascending departure requires slightly less ∆V than the descending departure on the order of 10 m/s. Subsequently, mass estimates are made for a Mars orbiter and a kick stage to determine if the desired ∆V is achievable with our eco-friendly in-space propulsion system when launched from our indigenous launch vehicle, KSLV-II.
ISSN:2226-4310
2226-4310
DOI:10.3390/aerospace10100827