Maintenance of Relay Orbit About the Earth-Moon Collinear Libration Points

Abstract

Relay orbits about the Earth-Moon collinear libration point shave significant valueon the exploration of the lunar farside, but have complex kinetic characteristics in the nature, thus the orbit maintenance has always been focused in the deep space navigation and control field. This paper explores orbit maintenance technology of the relay orbit about the collinear Earth-Moon libration points under the real dynamical conditions. First, based on the restricted three-body problem, the mathematic model of relay orbit station-keeping with the real dynamical model is analyzed. The continue-circling method is presented for the relay orbit maintenance with the two control styles, i.e., the Halo style and the Lissajous style. Second, with the third-body gravitation and the solar radiation pressure perturbations considered, the method is tested and analyzed by using the numerical simulations to achieve the control frequency and the corresponding velocity increment required by the relay orbits with different amplitudes. According to the simulations, the Lissajous style is suitable to the orbit maintenance with a control interval of 7.4 days and a velocity increment less than 20 m/s/a. Furthermore, the method has been successfully applied in Chang'e-2 and Chang'e-5T1 extended missions and can provide a beneficial reference for the future Chang'e-4 mission.

Keywords

libration point / orbit maintenance / restricted three-body problem / Halo orbit / Lissajous orbit

References

[1] Liu L, Liu Y, Cao J F, et al. CHANG'E-2 lunar escape maneuvers to the sun-earth L2 libration point mission[J]. Acta Astronautica, 2014(93):390-399.
[2] 刘磊,刘勇,曹建峰,等."嫦娥二号"探测小行星任务转移轨道设计[J].宇航学报,2014,35(3):262-268.[Liu L, Liu Y, Cao J F, et al. Mission design of the CHANG'E-2 asteroid exploration[J]. Journal of Astronautics, 2014,93:262-268.]
[3] Wu W R, Liu Y, Liu L, et al. Pre-LOI trajectory maneuvers of CHANG'E-2 libration point mission[J]. Science in China Series F:Information Sciences, 2012,55(6):1249-1258.
[4] 乔栋,黄江川,崔平远,等.嫦娥二号卫星飞越探测小行星的目标选择[J].中国科学:技术科学,2013,43(6):602-608.[Qiao D, Huang J C, Cui P Y, et al. Target choice of the CHANG'E-2 asteroid exploration[J]. Scientia Sinica Technologica, 2013,43(6):602-608.]
[5] 刘磊,唐歌实,胡松杰,等.月球探测再入返回试验后续飞行方案研究[J].宇航学报,2015,36(1):9-17.[Liu L, Tang G S, Hu S J, et al. Follow-up flight scheme for the reentry test of china lunar exploration[J]. Journal of Astronautics, 2015,36(1):9-17.]
[6] Keeter T M. Station-keeping strategies for librationpoint orbits:target point and floquet mode approaches[D]. West Lafayete, USA:Purdue University, 1994.
[7] Kulkarni J, Campbell M. Asymptotic stabilization of motion about an unstable orbit:application to spacecraft in halo orbit[C]//Proceeding of the 2004 American Control Conference. Boston, Massachusetts:IEEE, 2004:1025-1030.
[8] Moore A, Ober-Blöbaum S, Marsden J E. Optimization of spacecraft trajectories:a method combining invariant manifold techniques and discrete mechanics and optimal control[C]//The 19th AAS/AIAA Spaceflight Mechanics Meeting. Savannah, Georgia:AIAA, 2009.
[9] Howell K C, Pernicka H J. Numerical determination of Lissajous trajectories in the restricted three-body problem[J]. Celestial Mechanics, 1988,41:107-124.
[10] Folta D C, Woodard M A, Cosgrove D. Stationkeeping of the first earth-moon librationorbiters:the ARTEMIS mission[C]//AAS11-515.[S.l]:AIAA, 2011.