Preliminary Design and Analysis Status for Korea’s first Lunar Orbiter Mission
- Paper number
IAC-09.C1.5.3
- Author
Mr. Young-Joo Song, Yonsei Univ, Korea, Republic of
- Coauthor
Prof. Sang-Young Park , Yonsei Univ, Korea, Republic of
- Coauthor
Prof. Kyu-Hong Choi, Yonsei University, Korea, Republic of
- Coauthor
Dr. EunSup Sim, Korea Aerospace Research Institute, Korea, Republic of
- Coauthor
Ms. Jin Woo, Yonsei Univ, Korea, Republic of
- Year
2009
- Abstract
Attempts to expand the domain of Korean space program to explore outer planets are now under consideration. As for this, Korean government announced that Korea will launch the first lunar orbiter by 2020 and will attempt to land by 2025. In addition, government has already assigned to join the US-led International Lunar Network. However, most of the current Korean space technologies are now only focused to near Earth space program. Thus, the major purpose of this paper is to report the status of preliminary design and analysis results of Korea’s first lunar orbiter mission to international astronautical society. Under these motivations, development of Korea’s own preliminary lunar mission design software has just begun. Developed software is possible to design lunar missions from early stage of Earth departure phase, lunar capture and to the end of operational (mapping) phase. N-body dynamics is utilized to formulate the equations of motion including the gravitational effects of the Sun, Earth and Moon. In addition, accelerations due to geopotential, lunipotential harmonics and solar radiation pressures are implemented. To calculate exact positions and velocities of the planets, JPL's DE405 ephemeris is used. Using developed mission design software, the future Korea’s first lunar orbiter mission is preliminarily designed and analyzed. For the future Korea’s first lunar orbiter, launch vehicle is selected as KSLV-II(Korean Space Launch Vehicle-II) which is currently under development, and also Korea’s first Naro Space Center is considered as a launch site. Possible launch scenarios are investigated with achievable initial Earth parking orbits from Naro Space Center with KSLV-II. Also, Trans Lunar Injection strategy which guarantees the visibility of the explorer from Deajeon ground station is analyzed with numerous Earth-Moon transfer trajectory characteristics. Lunar orbit insertion strategy and capture sequences are also designed and analyzed to insert the orbiter to its operational orbit. Finally, lunar orbiter’s orbit maintenance strategy is also discussed during the required mission lifetimes. The design results presented in this paper includes launch opportunities, required optimal maneuver characteristics for every lunar mission phases, mass budgets as well as the trajectory characteristics and numerous related parameters. Although presented results are preliminary and have much more ways to go, the presented work will make great advances in Korean deep space program capabilities. Moreover, making clear addresses of the current Korea’s deep space program status to the international astronautical society, might be a good opportunities to find new collaborator of space business.
- Abstract document
- Manuscript document
(absent)