编队卫星相对位置测量信息自主确定月球引力场的方法

J4 ›› 2016, Vol. 38 ›› Issue (01): 125-130.

编队卫星相对位置测量信息自主确定月球引力场的方法

王祎1，杏建军1，于洋1，郑黎明1，赵延鹏1，刘琛2

(1.中南大学航空航天学院,湖南长沙 410083；2.国防科学技术大学航天科学与工程学院，湖南长沙 410073)

收稿日期:2014-08-11 修回日期:2015-03-06 出版日期:2016-01-25 发布日期:2016-01-25
基金资助:
中国博士后基金(20080440217,200902666);中南大学中央高校基本科研业务费专项资金(2013zzts264)

Autonomous lunar gravitational field determination via
relative position measurement of the satellite formation

WANG Yi1,XING Jianjun1,YU Yang1,ZHENG Liming1,ZHAO Yanpeng1,LIU Chen2

(1.School of Aeronautics and Astronautics,Central South University,Changsha 410083;2.College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

Received:2014-08-11 Revised:2015-03-06 Online:2016-01-25 Published:2016-01-25

摘要/Abstract

摘要：

针对月球远月面引力场的数据不能直接测量而导致其测量精度不高的问题，提出了一种基于双星编队的月球引力场自主确定方法。该方法考虑到月球引力场对编队卫星相对运动的影响，通过扩展卡尔曼滤波算法对星间距离测量数据的处理，利用观测量的测量值与一步预测测量值之间的偏差来修正一步预测状态值，从而得到状态估计量，即实现了卫星自主定轨以及月球引力场的自主确定。仿真结果表明，根据对编队卫星在7 430 s内的相对位置测量数据的处理，卫星轨道位置和速度确定精度分别能达到5.04 m和6.07×10-3 m/s；月球J2项摄动常数的精度能达到9.14×10-8；月球引力场常数的精度能达到3.47×107 m3/s2。此结果能在一定程度上改善现有的月球引力场模型，为我国“嫦娥工程”提供更多的技术资料。

关键词: 编队卫星, 引力场, J2项摄动, 相对位置, 扩展卡尔曼滤波, 月球

Abstract:

In view of the shortcoming that the data of the lunar back, cannot be directly measured and it leads to the low accuracy of the gravitational field, we propose an autonomous lunar gravitational field determination method based on dual satellite formation. Considering the effect of the lunar gravitational field on the relative position of satellite formation, the proposal adopts the extend Kalman filter (EKF) algorithm to handle the measurement data of satellite distance, and uses the difference between the measured data and the predicted data to modify the predicted status so as to obtain the estimate value of the status, thus realizing autonomous precise orbit determinations and determining the lunar gravitational field. The resulting system can achieve an orbital position accuracy of 5.04 m, an orbital velocity accuracy of 6.07×10-3 m/s, a gravity accuracy of 3.47×107 m3/s2 and the coefficient of a lunar perturbation accuracy of 9.14×10-8 in the time period of approximately 7 430 seconds. Simulation results verify the effectiveness of the program and improve the existing model of the lunar gravitational field to a certain extent. It can provide more technical information for the “Chang E Project” of China.

Key words: satellite formation;gravitational field;J2 perturbation;relative position;extend Kalman filter;lunar

王祎1，杏建军1，于洋1，郑黎明1，赵延鹏1，刘琛2. 编队卫星相对位置测量信息自主确定月球引力场的方法[J]. J4, 2016, 38(01): 125-130.

WANG Yi1,XING Jianjun1,YU Yang1,ZHENG Liming1,ZHAO Yanpeng1,LIU Chen2. Autonomous lunar gravitational field determination via
relative position measurement of the satellite formation [J]. J4, 2016, 38(01): 125-130.

参考文献［20］

［1］	Ouyang Ziyuan,Li Chunlai,Zhou Yongliao,et al. The primary science result from the Chang’E1 probe［J］. Sci China Earth Sci,2010,40(3):261280.(in Chinese)
［2］	Li Chunlai,Ren Xin,Liu Jianjun,et al. Laser altimetry data of Chang’E1 and the global lunar DEM model［J］. Sci China Earth Sci,2010,40(3):281293.(in Chinese)
［3］	Kato M,Sasaki S,Tanaka K,et al. The Japanese lunar mission SELENE:Science goals and present status［J］. Advance in Space Research,2008,42(2):294300.
［4］	Tanaka S,Shiraishi H,Kato M,et al. The science objectives of the SELENEⅡ mission as the post SELENE mission［J］. Advances in Space Research,2008,42(2):394401.
［5］	Song Laiyong,Qin Jian,Zeng Fanxiang. Lunar satellite gravity development history and recommendation on lunar exploration［J］. Journal of Geomatics,2013,38(6):6569.(in Chinese)
［6］	Yan Jianguo,Baur O,Li Fei,et al. Longwavelength lunar gravity field recovery from simulated orbit and intersatellite tracking data［J］. Advance in Space Research,2013,52(11):19191928.
［7］	Zheng Wei,Xu Houze,Zhong Min,et al. Demonstration of requirement for future lunar satellite gravity exploration mission based on interferometric laser intersatellite ranging principle［J］. Journal of Astronautics,2011,32(4):922932.(in Chinese)
［8］	Zhu Jun,Liao Ying,Wen Yuanlan. The integrated autonomous orbit determination of the navigation constellation based on crosslink range and groundbased emitter［J］. Journal of National University of Defense Technology,2009,31(2):1519.(in Chinese)
［9］	Liu Wanke,Gong Xiaoying，Li Zhenghang,et al. Combined orbit determination of navigation satellites with crosslink ranging observations and ground tracking observations［J］. Gromatics and Information Science of Wuhan University,2010,35(7):811815.(in Chinese)
［10］	Chen Jinping,You Zheng,Jiao Wenhai. Research on autonav of navigation satellite constellation based on crosslink range intersatellites orientation observation［J］. Journal of Astronautics,2005,26(1):4346. (in Chinese)
［11］	Eissfeller B,Zink T,Wolf R,et al. Autonomous satellite state determination by use of twodirectional links［J］. International Journal of Satellite Communications,2000,18(45):325346.
［12］	Rudenko S,Otten M,Visser P,et al. New improved orbit solutions for the ERS1 and ERS2 satellites［J］. Advances in Space Research,2012,49(8):12291244.
［13］	Ardaens J S,D’Amico S,Cropp A. GPSbased relative navigation for the Proba3 formation flying mission［J］. Acta Astronautica,2013,91:341355.
［14］	Psiaki M L. Absolute orbit and gravity determination using relative position measurements between two satellites［J］. Journal of Guidance,Control,and Dynamics,2011,34(5):12851297.
［15］	Sinha M,Gopinath N S, Malik N K. Lunar gravity field modeling critical analysis and challenges［J］. Advances in Space Research,2010,45(2):322349.
［16］	Li Litao,Yang Di,Cui Hutao. One method of calculating cislunar transfer trajecotry［J］. Journal of Astronautics,2003,24(2):150155.(in Chinese)
［17］	Xing Jianjun. Study on formation design and stationkeeping of spacecraft formation flying［D］. Changsha:National University of Defense Technology,2007.(in Chinese)
［18］	Wu Fei. A Kalman filter with online prarameter adjustment functionality and its application［J］. Compter Engineering & Science,2012,34(6):9396. (in Chinese)
［19］	Dong Lihong. Tension control system of scraper conveyor based on Kalman filter［J］. Computer Engineering & Science,2013,35(4):186190.(in Chinese)
［20］	Zhang Yan. Study On autonomous navigation of constellation using intersatellite measurement［D］. Changsha:National University of Defense Technology,2005. (in Chinese)
［21］	Liu Q,Kikuchi F,Matsumoto K,et al. Error analysis of samebeam differential VLBI technique using two SELENE satellites［J］. Advances in Space Research,2007,40(1):5157.
［22］	Goossens S,Matsumoto K,Liu Q,et al. Lunar gravity field determination using SELENE samebeam differential VLBI tracking data［J］. Journal of Geodesy,2011,85(4):205228.
	附中文参考文献:
［1］	欧阳自远,李春来,周永廖,等. 绕月探测工程的初步科学成果［J］. 中国科学:地球科学,2010,40(3):261280.
［2］	李春来,任鑫,刘建军,等. 嫦娥一号激光测距数据及全月球DEM模型［J］. 中国科学:地球科学,2010,40(3):281293.
［5］	宋来勇,秦建,曾凡祥. 月球重力场发展历程和我国月球探测建议［J］. 测绘地理信息,2013,38(6):6569.
［7］	郑伟,许厚择,钟敏,等. 基于激光干涉星间测距原理的下一代月球卫星重力测量计划需求论证［J］. 宇航学报,2011,32(4):922932.
［8］	朱俊,廖瑛,文援兰. 基于星间测距和地面发射源的导航星座整网自主定轨［J］. 国防科技大学学报,2009,31(2):1519.
［9］	刘万科,龚晓颖,李征航,等. 综合星间和地面测距数据的导航卫星联合定轨［J］. 武汉大学学报(信息科学版),2010,35(7):811815.
［10］	陈金平,尤政,焦文海. 基于星间距离和方向观测的导航卫星自主定轨研究［J］. 宇航学报,2005,26(1):4346.
［16］	李立涛,杨涤,崔祜涛. 奔月轨道的一种求解方法［J］. 宇航学报,2003,24(2):150155.
［17］	杏建军. 编队卫星周期性相对运动轨道设计与构形保持研究［D］. 长沙:国防科学技术大学,2007.
［18］	吴飞. 一种具有在线参数调整功能的Kalman滤波及其应用［J］. 计算机工程与科学,2012,34(6):9396.
［19］	董立红. 基于卡尔曼滤波的刮板输送机张力控制系统［J］. 计算机工程与科学,2013,35(4):186190.
［20］	张艳. 基于星间观测的星座自主导航方法研究［D］. 长沙:国防科学技术大学,2005.

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