Browse > Article
http://dx.doi.org/10.5140/JASS.2011.28.3.203

Analysis of Delta-V Losses During Lunar Capture Sequence Using Finite Thrust  

Song, Young-Joo (Space Application and Future Technology Center, Korea Aerospace Research Institute)
Park, Sang-Young (Astrodynamics and Control Laboratory, Department of Astronomy, Yonsei University)
Kim, Hae-Dong (Space Application and Future Technology Center, Korea Aerospace Research Institute)
Lee, Joo-Hee (Space Application and Future Technology Center, Korea Aerospace Research Institute)
Sim, Eun-Sup (Space Application and Future Technology Center, Korea Aerospace Research Institute)
Publication Information
Journal of Astronomy and Space Sciences / v.28, no.3, 2011 , pp. 203-216 More about this Journal
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 to be 100 km altitude with 90 degree of inclination. For the performance of the on-board thruster, three different performances (150 N with $I_{sp}$ of 200 seconds, 300 N with $I_{sp}$ of 250 seconds, 450 N with $I_{sp}$ of 300 seconds) are assumed, to provide a broad range of estimates of delta-V losses. As expected, it is found that the finite burn-arc sweeps almost symmetric orbital portions with respect to the perilune vector to minimize the delta-Vs required to achieve the final orbit. In addition, a difference of up to about 2% delta-V can occur during the lunar capture sequences with the use of assumed engine configurations, compared to scenarios with impulsive thrust. However, these delta-V losses will differ for every assumed lunar explorer's on-board thrust capability. Therefore, at the early stage of mission planning, careful consideration must be made while estimating mission budgets, particularly if the preliminary mission studies were assumed using impulsive thrust. The results provided in this paper are expected to lead to further progress in the design field of Korea's lunar orbiter mission, particularly the lunar capture sequences using finite thrust.
Keywords
optimal trajectory; lunar capture; lunar orbit insertion; finite thrust;
Citations & Related Records
Times Cited By KSCI : 11  (Citation Analysis)
연도 인용수 순위
1 Kato M, Sasaki S, Tanaka K, Iijima Y, Takizawa Y, The Japanese lunar mission SELENE: science goals and present status, AdSpR, 42, 294-300 (2008). http://dx.doi.org/10.1016/j.asr.2007.03.049   DOI
2 Zheng Y, Ouyang Z, Li C, Liu J, Zou Y, China's lunar exploration program: present and future, P&SS, 56, 881-886 (2008). http://dx.doi.org/10.1016/j.pss.2008.01.002   DOI
3 Tanaka S, Shiraishi H, Kato M, Okada T, The science objectives of the SELENE-II mission as the post SELENE mission, AdSpR, 42, 394-401 (2008). http://dx.doi.org/10.1016/j.asr.2007.07.002   DOI
4 The Boeing Company, SOCS user's guide release 7.0.2, M&CT-TECH-01-104 (The Boeing Company, Seattle, 2010), 529-543.
5 Vallado DA, McClain WD, Fundamentals of astrodynamics and applications, 3rd ed. (Kluwer Academic Publishers, Boston, 2007), 33-36.
6 Walker MJH, Ireland B, Owens J, A set modified equinoctial orbit elements, CeMec, 36, 409-419 (1985). http://dx.doi.org/10.1007/BF01227493   DOI
7 Woo J, Song YJ, Park SY, Kim HD, Sim ES, An earth-moon transfer trajectory design and analysis considering spacecraft's visibility from Daejeon ground station at TLI and LOI maneuvers, JASS, 27, 195-204 (2010). http://dx.doi.org/10.5140/JASS.2010.27.3.195   DOI   ScienceOn
8 Song YJ, Woo J, Park SY, Choi KH, Sim ES, The earth-moon transfer trajectory design and analysis using intermediate loop orbits, JASS, 26, 171-186 (2009c). http://dx.doi.org/10.5140/JASS.2009.26.2.171   DOI
9 Song YJ, Park SY, Choi KH, Sim ES, A lunar cargo mission design strategy using variable low thrust, AdSpR, 43, 1391-1406 (2009a). http://dx.doi.org/10.1016/j.asr.2009.01.020   DOI
10 Standish EM, JPL planetary and lunar ephemerides, DE405/LE405 (Jet Propulsion Laboratory, Los Angeles, 1998), 1-6.
11 Song YJ, Park SY, Choi KH, Sim ES, Optimal earth-moon trajectory design using constant and variable low thrust, J. Korean Soc. Aeronaut. Sci., 37, 843-854 (2009b).   과학기술학회마을   DOI   ScienceOn
12 Song YJ, Park SY, Kim HD, Joo HL, Sim ES, Trans Lunar Injection (TLI) maneuver design and analysis using finite thrust, J. Korean Soc. Aeronaut. Sci., 38, 998-1011 (2010a).   과학기술학회마을   DOI   ScienceOn
13 Song YJ, Park SY, Kim HD, Sim ES, Development of precise lunar orbit propagator and lunar polar orbiter's lifetime analysis, JASS, 27, 97-106 (2010b). http://dx.doi.org/10.5140/JASS.2010.27.2.097   DOI   ScienceOn
14 Kechichian JA, Minimum-time constant acceleration orbit transfer with first-order oblateness effect, JGCD, 23, 595-603 (2000).   DOI   ScienceOn
15 Song YJ, Park SY, Choi KH, Sim ES, Development of Korean preliminary lunar mission design software, J. Korean Soc. Aeronaut. Sci., 36, 357-367 (2008).   과학기술학회마을   DOI
16 Lee DH, Bang HC, Low thrust, fuel optimal earth escape trajectories design, J. Korean Soc. Aeronaut. Sci., 35, 647-654 (2007).   과학기술학회마을   DOI
17 Lozier D, Galal K, Folta D, Beckman M, Lunar pospector mission design and trajectory support (AAS 98-323), in Proceedings of the AAS/GSFC International Symposium on Space Flight Dynamics, Greenbelt, MD, 11-15 May 1998, 297-311.
18 No TS, Jeon GE, A study on optimal earth-moon transfer orbit design using mixed impulsive and continuous thrust, J. Korean Soc. Aeronaut. Sci., 38, 684-692 (2010).   과학기술학회마을   DOI   ScienceOn
19 Chin G, Brylow S, Foote M, Garvin J, Kasper J, et al., Lunar Reconnaissance Orbiter overview: the instrument suite and mission, SSRv, 129, 391-419 (2007). http://dx.doi.org/10.1007/s11214-007-9153-y   DOI
20 Betts JT, Practical methods for optimal control and estimation using nonlinear programming, 2nd ed. (Society for Industrial and Applied Mathematics, Philadelphia, 2010), 152-165.
21 Cho DH, Jeong BY, Lee DH, Bang HC, Optimal perilune altitude of lunar landing trajectory, IJASS, 10, 67-74 (2009).   과학기술학회마을   DOI
22 Cho DH, Jung YS, Lee DH, Jung BY, Bang HC, Satellite trajectory correction maneuver for lunar mission based on three-body dynamics, J. Korean Soc. Aeronaut. Sci., 38, 875-881 (2010).   과학기술학회마을   DOI
23 Goswamia JN, Annaduraib M, Chandrayaan-1 mission to the Moon, AcAau, 63, 1215-1220 (2008). http://dx.doi.org/10.1016/j.actaastro.2008.05.013   DOI
24 Jeong BY, Choi YH, Jo SJ, Bang HC, Terrain aided inertial navigation for precise planetary landing, J. Korean Soc. Aeronaut. Sci., 38, 673-745 (2010).   과학기술학회마을   DOI