Optimal Lunar Point Return Orbit Design and Analysis via a Numerical Three-Step Approach
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ORIGINAL PAPER
Optimal Lunar Point Return Orbit Design and Analysis via a Numerical Three-Step Approach Yongjun Song1 · Young-Joo Song2 · Kap-Sung Kim1 · Ho Jin1 · Donghun Lee2 Received: 8 May 2019 / Revised: 30 December 2019 / Accepted: 9 January 2020 © The Korean Society for Aeronautical & Space Sciences 2020
Abstract Herein, the characteristics of the Moon-to-Earth (M–E) trajectory satisfying the point return orbit (PRO) conditions are analyzed and optimized. A numerical three-step approach is proposed to serve as a useful tool to generate trajectory while preparing for real-world missions. To formulate the given problem, each step properly adapts different equations of motion with design parameters suitable to each step’s primary objective. Three- and N-body equations of motion are used as a basis, and PRO is constrained by the parking orbit at the Moon and Earth re-entry corridor associated with the re-entry position. Consequently, the major trans-Earth-injection (TEI) maneuver condition at the Moon is optimized together with the right ascension of the ascending node and the argument of the latitude. Moreover, the TEI maneuver magnitude with its execution date and required time of flight is optimized to form PRO. Adopting this three-step approach, the effect of the Moon’s relative motion with respect to the Earth to form the optimal TEI condition is clearly analyzed. In addition, direct insight on the TEI condition is obtained by expressing the M–E rotating frame, which is expected to save time and effort while generating initial guesses for TEI conditions. Keywords Moon-to-Earth trajectory · Earth return trajectory · Lunar exploration · Earth re-entry
1 Introduction Over the last decade, several lunar exploration missions have been undertaken worldwide. Korea has also announced the second Basic Plan for Promotion of Space Development in November 2011 that includes the road map for the planetary exploration missions. Based on this plan, Korea began preparing for a lunar exploration mission in 2013 with plans to launch the first experimental lunar orbiter, the Korea Pathfinder Lunar Orbiter (KPLO), by the end of 2020 [1]. After completing the KPLO mission, future missions will focus on lunar surface investigations using landers and rovers. According to Korea’s third Basic Plan for Promotion of Space Development, additional standard reviews for these Moon-landing missions will be conducted from 2019. Accordingly, significant research on trajectory design has
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Ho Jin [email protected]
1
School of Space Research, Kyung Hee University, Yongin 17410, Republic of Korea
2
Korea Aerospace Research Institute, Daejeon 305-806, Republic of Korea
been performed to prepare for the long-term Korean lunar exploration [1]. However, considerable research conducted thus far has focused on the trajectory design for lunar orbiting or landing missions; to complete the lunar exploration, the return mission must be extensively researched because it is the last major phase of the Moon exploration and can maximize both the sci
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