An introduction to the lunar and planetary science activities in Korea

Kim, Kyeong Ja; Seo, Hye Sook; Ju, Gwanghyeok; Lee, Sang-Ryool; Choi, Gi-Hyuk; Sim, Eun-Sup; Lee, Tai Sik

doi:10.1016/j.asr.2013.05.009

Cited by 5 publications

(2 citation statements)

References 14 publications

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“…However, because most lunar simulants consist largely of crushed basalt and volcanic ash, and chemical synthesis has been employed to increase their iron (Fe) content [e.g., JSC-1 = US$19/kg; Japan's Fuji Japanese Simulant 1 (FJS-1) = US$4/kg], they are expensive and thus less versatile. In Korea, some attempts were made to develop lunar simulants in 2010 (Hanyang University) and 2014 (Korea Aerospace University) (Kim et al 2014;Yoo et al 2014), but their geotechnical behaviors were insufficient to satisfy international standards.…”

Section: Introductionmentioning

confidence: 99%

Development and Geotechnical Engineering Properties of KLS-1 Lunar Simulant

2018

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Lunar exploration, which slowed in the 21st century after the Apollo program, has seen more activity recently with the participation of Asian countries such as Japan, China, and India. Because lunar modules and rovers cannot be tested directly on lunar soil, these countries have developed lunar simulants. Simulating lunar soil is difficult and expensive because its formation mechanism and geotechnical behavior are comprehensively different from those of the terrestrial soil. Johnson Space Center Number One (JSC-1) and Johnson Space Center Number One A (JSC-1A), developed by the National Aeronautics and Space Administration, are the most widely used simulants. Korea has yet to succeed in developing a lunar simulant that meets international standards. The authors perform basic research on lunar simulant development based on basalt samples having similar chemical and mechanical properties to those of lunar soil, with reference to lunar soil data reported under the Apollo program. The resulting prototype is named Korea Lunar Stimulant-Type 1 (KLS-1). Compared with other lunar simulants [JSC-1 and Fuji Japanese Simulant 1 (FJS-1)], KLS-1 shows promise in terms of affordability and similarity to real lunar soil. As such, it is expected to find a wide variety of applications not only in space development projects but also in international research.

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Section: Introductionmentioning

confidence: 99%

Development and Geotechnical Engineering Properties of KLS-1 Lunar Simulant

2018

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“…Therefore, the Korean aeronautical and space science community has performed numerous related mission studies, and the Korea Aerospace Research Institute (KARI) is performing pre-phase work for the lunar mission. Several preliminary design studies have already been conducted, such as an optimal transfer trajectory analysis [7][8][9][10][11][12][13][14][15][16], mapping orbit analysis [17], landing trajectory analysis [18,19], contact schedule analysis [20,21], link budget analysis [22][23][24], lander/rover system design [25][26][27][28][29], and candidate payload design analysis [30]. Before 2020, the first Korean lunar pathfinder orbiter mission is scheduled for launch around 2017 with international collaboration.…”

Section: Introductionmentioning

confidence: 99%

Lunar CubeSat Impact Trajectory Characteristics as a Function of Its Release Conditions

Song

Jin

Garick-Bethell

2015

Mathematical Problems in Engineering

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As a part of early system design activities, trajectory characteristics for a lunar CubeSat impactor mission as a function of its release conditions are analyzed. The goal of this mission is to take measurements of surface magnetic fields to study lunar magnetic anomalies. To deploy the CubeSat impactor, a mother-ship is assumed to have a circular polar orbit with inclination of 90 degrees at a 100 km altitude at the Moon. Both the in- and out-of-plane direction deploy angles as well as delta-Vmagnitudes are considered for the CubeSat release conditions. All necessary parameters required at the early design phase are analyzed, including CubeSat flight time to reach the lunar surface, impact velocity, cross ranges distance, and associated impact angles, which are all directly affected by the CubeSat release conditions. Also, relative motions between these two satellites are analyzed for communication and navigation purposes. Although the current analysis is only focused on a lunar impactor mission, the methods described in this work can easily be modified and applied to any future planetary impactor missions with CubeSat-based payloads.

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