Ground Contact Analysis for Korea's Fictitious Lunar Orbiter Mission

Song, Young Woong; Ahn, Sangtae; Choi, Su-Jin; Sim, Eun-Sup

doi:10.5140/jass.2013.30.4.255

Cited by 5 publications

(5 citation statements)

References 18 publications

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“…Choi et al (2017) performed trajectory optimization using the pattern search method to minimize the delta-V magnitude required for Earth-Moon direct transfer. Song et al (2013) analyzed the ground contact opportunity for the fictitious low lunar orbiter to prepare for a future Korean lunar orbiter mission. In the analysis of Song et al (2013), four KOMPSAT ground stations are assumed to be the Korean future near earth networks to support lunar missions, and worldwide separated DSNs are also included during the contact availability analysis.…”

Section: Past Efforts: Starting With Mars Mission Trajectory Designmentioning

confidence: 99%

“…Song et al (2013) analyzed the ground contact opportunity for the fictitious low lunar orbiter to prepare for a future Korean lunar orbiter mission. In the analysis of Song et al (2013), four KOMPSAT ground stations are assumed to be the Korean future near earth networks to support lunar missions, and worldwide separated DSNs are also included during the contact availability analysis. Similar analyses were conducted by Song et al (2014a) that focused more on lunar transfer and capture phases.…”

Section: Past Efforts: Starting With Mars Mission Trajectory Designmentioning

confidence: 99%

See 1 more Smart Citation

Flight Dynamics and Navigation for Planetary Missions in Korea: Past Efforts, Recent Status, and Future Preparations

Song¹,

Lee²,

Bae³

et al. 2018

Journal of Astronomy and Space Sciences

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In spite of a short history of only 30 years in space development, Korea has achieved outstanding space development capabilities, and became the 11th member of the “Space Club” in 2013 by launching its own satellites with its own launch vehicle from a local space center. With the successful development and operation of more than 10 earth-orbiting satellites since 1999, Korea is now rapidly expanding its own aspirations to outer space exploration. Unlike earth-orbiting missions, planetary missions are more demanding of well-rounded technological capabilities, specifically trajectory design, analysis, and navigation. Because of the importance of relevant technologies, the Korean astronautical society devoted significant efforts to secure these basic technologies from the early 2000s. This paper revisits the numerous efforts conducted to date, specifically regarding flight dynamics and navigation technology, to prepare for future upcoming planetary missions in Korea. However, sustained efforts are still required to realize such challenging planetary missions, and efforts to date will significantly advance the relevant Korean technological capabilities.

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Section: Past Efforts: Starting With Mars Mission Trajectory Designmentioning

confidence: 99%

Section: Past Efforts: Starting With Mars Mission Trajectory Designmentioning

confidence: 99%

Flight Dynamics and Navigation for Planetary Missions in Korea: Past Efforts, Recent Status, and Future Preparations

Song¹,

Lee²,

Bae³

et al. 2018

Journal of Astronomy and Space Sciences

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“…Therefore, the Korean aeronautical and space science community has performed numerous related mission studies. Several preliminary design studies have already been conducted, such as an transfer trajectory analysis (Song et al 2009(Song et al , 2011Woo et al 2010), contact schedule analysis (Song et al 2013(Song et al , 2014, rover system design (Kim et al 2009, Eom et al 2012.…”

Section: Introductionmentioning

confidence: 99%

Evaluating High-Degree-and-Order Gravitational Harmonics and its Application to the State Predictions of a Lunar Orbiting Satellite

Song

Kim²

2015

Journal of Astronomy and Space Sciences

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In this work, an efficient method with which to evaluate the high-degree-and-order gravitational harmonics of the nonsphericity of a central body is described and applied to state predictions of a lunar orbiter. Unlike the work of Song et al. (2010), which used a conventional computation method to process gravitational harmonic coefficients, the current work adapted a well-known recursion formula that directly uses fully normalized associated Legendre functions to compute the acceleration due to the non-sphericity of the moon. With the formulated algorithms, the states of a lunar orbiting satellite are predicted and its performance is validated in comparisons with solutions obtained from STK/Astrogator. The predicted differences in the orbital states between STK/Astrogator and the current work all remain at a position of less than 1 m with velocity accuracy levels of less than 1 mm/s, even with different orbital inclinations. The effectiveness of the current algorithm, in terms of both the computation time and the degree of accuracy degradation, is also shown in comparisons with results obtained from earlier work. It is expected that the proposed algorithm can be used as a foundation for the development of an operational flight dynamics subsystem for future lunar exploration missions by Korea. It can also be used to analyze missions which require very close operations to the moon.

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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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Ground Contact Analysis for Korea's Fictitious Lunar Orbiter Mission

Cited by 5 publications

References 18 publications

Flight Dynamics and Navigation for Planetary Missions in Korea: Past Efforts, Recent Status, and Future Preparations

Flight Dynamics and Navigation for Planetary Missions in Korea: Past Efforts, Recent Status, and Future Preparations

Evaluating High-Degree-and-Order Gravitational Harmonics and its Application to the State Predictions of a Lunar Orbiting Satellite

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

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