2011
DOI: 10.5140/jass.2011.28.3.203
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Analysis of Delta-V Losses During Lunar Capture Sequence Using Finite Thrust

Abstract: To prepare for a future Korean lunar orbiter mission, semi-optimal lunar capture orbits using finite thrust are designed and analyzed. Finite burn delta-V losses during lunar capture sequence are also analyzed by comparing those with values derived with impulsive thrusts in previous research. To design a hypothetical lunar capture sequence, two different intermediate capture orbits having orbital periods of about 12 hours and 3.5 hours are assumed, and final mission operation orbit around the Moon is assumed t… Show more

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Cited by 10 publications
(12 citation statements)
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“…In (13) and (14), Q 2 is the direction cosine matrix that transforms a vector from LVLH frame attached to the CubeSat impactor to the CubeSat centered MME2000 frame defined in (15). In (15), subscripts Cube , Cube , and Cube denote the unit vector components of R Cube defined in the M-MME2000 frame 6 Mathematical Problems in Engineering…”
Section: Relative Motion Between the Mother-ship And Cubesatmentioning
confidence: 99%
See 1 more Smart Citation
“…In (13) and (14), Q 2 is the direction cosine matrix that transforms a vector from LVLH frame attached to the CubeSat impactor to the CubeSat centered MME2000 frame defined in (15). In (15), subscripts Cube , Cube , and Cube denote the unit vector components of R Cube defined in the M-MME2000 frame 6 Mathematical Problems in Engineering…”
Section: Relative Motion Between the Mother-ship And Cubesatmentioning
confidence: 99%
“…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%
“…e approaches for solving a trajectory optimization problem can be categorized into two methods: direct or indirect [15][16][17][18][19][20][21][22]. In the indirect method, the optimization problem is converted into a multipoint boundary value problem, and the optimal thrust magnitude and direction are determined by finding unknown state and costate variables.…”
Section: Introductionmentioning
confidence: 99%
“…Finally, a spacecraft will perform several lunar orbit insertion (LOI) maneuvers to be captured and orbit around the moon at the desired mission orbit altitude. Several preliminary design studies have already been conducted for the lunar mission trajectory design and analysis (Song et al 2008(Song et al , 2009Woo et al 2010;Song et al 2011;Choi et al 2013). Nevertheless, these design studies were primarily focused on generating the optimal trajectory, namely the nominal trajectory planning points of view for the maneuvers listed above.…”
Section: Introductionmentioning
confidence: 99%