Analysis on the Orbit Determination of Longjiang-2 Lunar Microsatellite

OUYANG Qi, NIU Dongwen

PDF(1172 KB)
PDF(1172 KB)
Journal of Deep Space Exploration ›› 2019, Vol. 6 ›› Issue (3) : 254-260. DOI: 10.15982/j.issn.2095-7777.2019.03.009
Topic:Orbit Determination and Control Technology for Deep Space Exploration

Analysis on the Orbit Determination of Longjiang-2 Lunar Microsatellite

  • OUYANG Qi, NIU Dongwen
Author information +
History +

Abstract

The TT&C (Tracking Telemetry and Command) resources are usually limited for the deep space exploration mission of micro-nano satellites. It is necessary to analyze the orbit determination accuracy under the limited resource of TT&C. The orbit determination precision of Longjiang-2 lunar microsatellite is analyzed. Longjiang-2 microsatellite only has USB orbital measurement data, and the TT&C resources in the lunar phase are relatively tight. There are two stations are used to track the Longjiang-2 satellite every day,and a total of about 3-4 hours of orbital measurement data is available. Firstly,the Longjiang-2 mission is introduced and the factors which have effect on orbit determination are presented. Secondly, the dynamical model is given. The orbit determination precision of earth-moon transfer orbit is analyzed. Lastly,the effects of perturbative force, wheeloff loading and data arc length are studied and then the orbit determination strategy is proposed. The orbit determination precision of lunar orbit is given. The conclusions can provide useful reference for the future deep space exploration mission of micro-nano satellites.

Keywords

micro-nano satellite / deep space exploration / orbit determination

Cite this article

Download citation ▾
OUYANG Qi, NIU Dongwen. Analysis on the Orbit Determination of Longjiang-2 Lunar Microsatellite. Journal of Deep Space Exploration, 2019, 6(3): 254‒260 https://doi.org/10.15982/j.issn.2095-7777.2019.03.009

References

[1] 杨维维. 快速机动小卫星总体设计及控制技术研究[D]. 长沙:国防科学技术大学,2006. YANG W W. Research on overall design and control technology of small satellite with rapid maneuver ability[D]. Changsha:National University of Defense Technology, 2006.
[2] WALL M. Tiny Cubesats set to explore deep space[EB/OL].[2018-12-20]. http://www.space.com/29306-cubesats-deep-space-exploration.html.
[3] 冯粒,袁勃."龙江2号"微卫星成功传回月球图像[EB/OL].[2018-12-20]. http://scitech.people.com.cn/n1/2018/0615/c1007-30061484.html.
[4] 张锦绣,陈学雷,曹喜滨,等. 月球轨道编队超长波天文观测微卫星任务[J]. 深空探测学报,2017,4(2):158-165. ZHANG J S, CHEN X L, CAO X B, et al. Formation flying around lunar for ultra-long wave radio interferometer mission[J]. Journal of Deep Space Exploration, 2017, 4(2):158-165.
[5] 黄勇,胡小工,董光亮,等. 动量轮卸载对环月卫星SMART-1轨道的影响和定轨策略[J]. 飞行器测控学报, 2007,26(5):62-66. HUANG Y, HU X G, DONG G L, et al. The effect of wheel off-loading on the orbit of lunar satellite SMART-1[J].Journal of Spacecraft TT&C Technology, 2007, 26(5):62-66.
[6] TAPLER B D, SCHUTZ B E, BORN G H. Statistical orbit determination[M]. Holland:Eleservier academic press, 2004.
[7] 李济生. 人造卫星精密轨道确定[M]. 北京:解放军出版社,1995.
[8] 陈明,唐歌实,曹建峰,等. 嫦娥一号绕月探测卫星精密定轨实现[J]. 武汉大学学报,2011,36(2):212-216. CHEN M, TANG G S, CAO J F, et al. Precision orbit determination of CE-1 lunar satellite[J]. Wuhan:Geomatics and Information Science of Wuhan University, 2011, 36(2):212-216.
[9] 段建锋,曹建峰,张宇,等. 一种有效提高CE-1卫星卸载前后精密星历衔接精度的定轨策略[J]. 航天控制, 2015,33(1):66-71. DUAN J F, CAO J F, ZHANG Y, et al. An effective orbit determination strategy to improve the cohesion precision of Chang'e one satellite's precise ephemeris before and after unloading[J]. Aerospace Control, 2015, 33(1):66-71.
[10] 张宇,曹建峰,段建锋,等. 嫦娥三号探测器连续姿控的轨道动力学模型补偿及实现[J]. 宇航学报,2015,36(5):489-495. ZHANG Y, CAO J F, DUAN J F, et al. Orbit dynamics model compensation and implementation for continuous control of Chang'e 3 probe[J]. Journal of Astronautics, 2015, 36(5):489-495.
PDF(1172 KB)

Accesses

Citations

Detail

Sections
Recommended

/