ExoMars/TGO Science Orbit Design

Long, Stacia M.; Lyons, Daniel T.; Guinn, J.; Lock, Rob

doi:10.2514/6.2012-4881

Cited by 1 publication

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“…Since NASA's Mariner 4 first reached Mars in 1964, global efforts have been made to explore Mars, including the Mars reconnaissance orbiter (MRO) in 2005 and the Mars atmosphere and volatile evolution (MAVEN) in 2013 [2,3]. Europe has sent missions such as Mars Express in 2003 and ExoMars in 2016; India launched Mangalyaan in 2013; the UAE conducted the Emirates Mars Mission (EMM) in 2020; and China sent Tianwen-1 to Mars in 2020 [4][5][6][7][8]. In this situation, South Korea needs to determine what kind of Mars exploration is possible based on our infrastructure, such as the launch site and deep space link in our country, as well as the recently developed KSLV-II and eco-friendly in-space propulsion system for exploration.…”

Section: Introductionmentioning

confidence: 99%

A Pattern Search Method to Optimize Mars Exploration Trajectories

Choi,

Kang,

Lee

et al. 2023

Aerospace

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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.

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