Transfers analysis of deploying a retrograde GEO monitorsatellite by Moon swing-by

doi:10.16708/j.cnki.1000.758X.2021.0032

Chinese Space Science and Technology ›› 2021, Vol. 41 ›› Issue (3): 9-15.doi: 10.16708/j.cnki.1000.758X.2021.0032

Previous Articles Next Articles

Transfers analysis of deploying a retrograde GEO monitorsatellite by Moon swing-by

HE Boyong^1,2,*，MA Pengbin¹，DU Weibing¹，LI Hengnian¹

1 State Key Laboratory of Astronautic Dynamics, Xi′an Satellite Control Center，Xi′an 710043,China
2 School of Astronautics，Northwestern Polytechnical University，Xi′an 710072，China

Received:2020-08-06 Revised:2020-09-08 Accepted:2020-12-30 Published:2021-06-25 Online:2021-06-25
Contact: Email: heboyong@yeah.net E-mail:heboyong@yeah.net

Abstract

Abstract: Retro-GEO refers to the retrograde geostationary Earth orbit (GEO), which has the same or similar height as that of the GEO, but with an inclination of 180 °. A monitorsatellite on retroGEO can give early debris warning for the GEO assets every 12 hours. RetroGEO launched directly in the westward has great difficulties in ground tracking and control, as well as launch energy cost. Based on a four body model, and in order to reduce the sensitivity of design variables, a transfer to retro-GEO design model by the Moon swing by was proposed applying the trans-lunar orbital elements at the moment of perilune. The result obtanined by using orbital dynamics model continuation shows a natural property of such orbits, that is the return duration from perilune must be about 114.79 hours. The conclusion can be used to solve this kind of orbit with a high precision orbital dynamics model.

Key words: retrograde GEO, debris warning, orbit design, Moon swingby, model continuation

CLC Number:

V412.4

HE Boyong, MA Pengbin, DU Weibing, LI Hengnian. Transfers analysis of deploying a retrograde GEO monitorsatellite by Moon swing-by[J]. Chinese Space Science and Technology, 2021, 41(3): 9-15.

Add to citation manager EndNote|Reference Manager|ProCite|BibTeX|RefWorks

URL: https://journal26.magtechjournal.com/kjkxjs/EN/10.16708/j.cnki.1000.758X.2021.0032

https://journal26.magtechjournal.com/kjkxjs/EN/Y2021/V41/I3/9

[1]	CHEN Shiyu, NI Yanshuo, PENG Jing. Orbit design method of near-lunar space constellation [J]. Chinese Space Science and Technology, 2024, 44(3): 15-29.
[2]	YANG Mengfei, DAI Shuwu, WANG Ying, ZHU Chenglin, YANG Shangbin, ZHANG Yechi. Progress and prospect of solar exploration in space [J]. Chinese Space Science and Technology, 2022, 42(5): 1-10.
[3]	LU Lin, LI Haiyang, LIU Jianghui, YANG Luyi. Design of point return orbit for human lunar polar exploration mission [J]. Chinese Space Science and Technology, 2020, 40(5): 61-71.
[4]	Yang-Hong-Wei, CHEN Yang, BAO Yin-He-Xi, LI Jun-Feng. Trajectory Design of Gravity Assist in the High-fidelity Dynamic Model [J]. Chinese Space Science and Technology, 2013, 33(2): 1-6.
[5]	LIU Lei, LIU Yong, CAO Jian-Feng, TANG Ge-Shi, HU Song-Jie. Kinetic Characteristics and Continuation Algorithm of Periodic Families [J]. Chinese Space Science and Technology, 2013, 33(1): 30-36.
[6]	ZHANG Lei, YU Deng-Yun, ZHANG He. Preliminary Design and Characteristic Analysis of Moon-to-Earth Transfer Trajectories [J]. Chinese Space Science and Technology, 2011, 31(3): 62-70.
[7]	CHEN Yang, ZHAO Guo-Qiang, BAOYin He-Xi, LI Jun-Feng. Orbit Design for Mars Exploration by the Accurate Dynamic Model [J]. Chinese Space Science and Technology, 2011, 31(1): 8-15.

Transfers analysis of deploying a retrograde GEO monitorsatellite by Moon swing-by

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 7

Recommended Articles

Metrics

Comments