低轨卫星广播星历参数设计
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摘要
导航增强卫星从高轨拓展到低轨(Low Earth Orbit,LEO),需要针对低轨卫星设计可靠的广播星历参数模型。传统的广播星历主要针对中高轨卫星设计,如果直接用于受摄动力更复杂的LEO卫星,星历拟合的URE精度难以达到要求。针对低轨卫星的受力特性,在ECEF坐标系内分别利用多项式和多项式+周期项2种方案来进行经验力(除地球扁率以外的摄动力)建模,设计了2种基于轨道列表型的16参数广播星历参数模型;将拟合时间设定为卫星的地面最大可见时间,以减少用户更新星历频率。300～1 500 km高度的轨道拟合实验表明,利用多项式+周期项建立经验力的16参数星历拟合精度更高,其R/T/N三个方向拟合误差分别优于10/10/3 cm,URE优于9 cm。
It is necessary to design a reliable broadcast ephemeris for LEO satellite when the navigation augmentation satellites expand from high orbit to low orbit.The traditional broadcast ephemeris is mainly designed for medium and high orbit satellites.If it is directly used for LEO satellites with more complex perturbations,it will be difficult for the URE accuracy of ephemeris fitting to meet the requirements.Considering the force characteristics of LEO satellites,the empirical force(perturbation force except the earth oblateness) is modeled by using polynomial and periodic terms in ECEF coordinate system,and two 16-parameter broadcast ephemeris parameter models based on orbital list are designed.The fitting time is set as the maximum visible time of the satellite to the ground to reduce the user's ephemeris updating frequency.The orbital fitting experiments at altitudes of 300～1 500 km show that the 16-parameter ephemeris using polynomial plus periodic term to establish empirical force has higher fitting accuracy,and the fitting errors of R/T/N in three directions are better than 10/10/3 cm respectively,and the URE is better than 9 cm.
It is necessary to design a reliable broadcast ephemeris for LEO satellite when the navigation augmentation satellites expand from high orbit to low orbit.The traditional broadcast ephemeris is mainly designed for medium and high orbit satellites.If it is directly used for LEO satellites with more complex perturbations,it will be difficult for the URE accuracy of ephemeris fitting to meet the requirements.Considering the force characteristics of LEO satellites,the empirical force(perturbation force except the earth oblateness) is modeled by using polynomial and periodic terms in ECEF coordinate system,and two 16-parameter broadcast ephemeris parameter models based on orbital list are designed.The fitting time is set as the maximum visible time of the satellite to the ground to reduce the user's ephemeris updating frequency.The orbital fitting experiments at altitudes of 300～1 500 km show that the 16-parameter ephemeris using polynomial plus periodic term to establish empirical force has higher fitting accuracy,and the fitting errors of R/T/N in three directions are better than 10/10/3 cm respectively,and the URE is better than 9 cm.
引文
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[26] 陈刘成,胡小工,陈娉娉,等.工程化广播星历参数拟合算法与接口设计[C]//中国测绘学会第九次全国会员代表大会,2009:18-23..
[27] 张中凯,杜兰,刘利,等.GEO广播星历参数设计的无奇点根数法[J],测绘学报,2014,43(5):452-457.
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[2] 陈锋,郭道省,刘爱军,等.GEO卫星移动通信系统发展状况及趋势分析[C]//卫星通信学术年会,2012:1-5.
[3] 余海翔.浅谈卫星移动通信系统[J].信息通信,2000(1):13-18.
[4] MAO Y,DU Y,SONG X Y,et al.GEO and IGSO Joint Precise Orbit Determination[J].Science China Physics,Mechanics & Astronomy,2011,54(6):1009-1013.
[5] LI X J,ZHOU J H,HU X G,et al.Orbit Determination and Prediction for Beidou GEO Satellites at the Time of the Spring/Autumn Equinox[J].Science China Physics,Mechanics & Astronomy,2015,58(8):1-9.
[6] CHOI J Y,LEE S J.Precision Assessment of Near Real Time Precise Orbit Determination for Low Earth Orbiter[J].Journal of Astronomy & Space Sciences,2011,28(1):55-62.
[7] MONTENBRUCK O,GILL E,KROES R.Rapid Orbit Determination of LEO Satellites Using IGS Clock and Ephemeris Products[J].GPS Solutions,2005,9(3):226-235.
[8] ENGE P ,FERRELL B ,BENNETT J,et al.Orbital Diversity for Satellite Navigation[C]//Proceedings of the 25th International Technical Meeting of the Satellite Division of the Institute of Navigation (ION GNSS 2012),Nashville,TN,2012:3834-3846.
[9] 赵金峰,于笑,冯少栋,等.基于LEO增强的COMPASS系统设计及性能分析[J].电讯技术,2013,53(2):131-135.
[10] 刘志俭,温日红,葛侠,等.GNSS导航电文结构及广播星历分析与设计[C]//中国卫星导航学术年会,2011:166-170.
[11] Navstar GPS Space Segment/Navigation User Interfaces:Interface Specification IS-GPS-200 Revision H[S],2014.
[12] Administrator Office of China Satellite Navigation.BeiDou Navigation Satellite System Signal in Space Interface Control Document Open Service Signal B1I-1.0:BDS-SIS-ICD[S/OL].2012,http://www.beidou.gov.cn.
[13] Global Navigation Satellite System GLONASS,Interface Control Document.Navigational Radio Signal in bands L1,L2[S],2008.
[14] MLAKAR P.Global Navigation Satellite Systems[J].Computers & Electronics in Agriculture,2005,25(1):67-85.
[15] 马开锋,彭碧波,洪樱.基于卫星轨道特征的低轨卫星星历参数拟合法[J].大地测量与地球动力学,2007,27(1):85-90.
[16] REID T G R,NEISH A M,WALTER T F,et al.Leveraging Commercial Broadband LEO Constellations for Navigation[C]//The International Technical Meeting of the Satellite Division of the Institute of Navigation.2016:1-15.
[17] 方善传,杜兰,周佩元,等.低轨导航增强卫星的轨道状态型星历参数设计[J].测绘学报,2016,45(8):904-910.
[18] 郝金明.利用地面测轨资料拟合GPS广播星历[J].测绘科学技术学报,1990(1):24-27.
[19] 吴宅莲,吴会英,刘国华.GPS广播星历参数算法研究[C]//中国卫星导航学术年会,2011:1-4.
[20] 刘光明,廖瑛,文援兰,等.导航卫星广播星历参数拟合算法研究[J].国防科技大学学报,2008,30(3):100-104.
[21] 许承东.GNSS数学仿真原理及系统实现[M].北京:中国宇航出版社,2014.
[22] 葛奎,王解先.GLONASS卫星位置计算与程序实现[J].测绘与空间地理信息,2009,32(2):19-22.
[23] ICD-GLONASS,Version 5.1[S/OL].Russian institute of space devise engineering,2008.http://rniikp.ru/en/pages/about/publ/ICD_GLONASS_eng.pdf.
[24] 葛茂荣,过静珺.GLONASS卫星坐标的计算方法[J].测绘通报,1999(2):2-4.
[25] 郭睿,周建华,胡小工,等.一种地球静止轨道卫星的快速恢复定轨方法[J].测绘学报,2011,40(s1):19-25.
[26] 陈刘成,胡小工,陈娉娉,等.工程化广播星历参数拟合算法与接口设计[C]//中国测绘学会第九次全国会员代表大会,2009:18-23..
[27] 张中凯,杜兰,刘利,等.GEO广播星历参数设计的无奇点根数法[J],测绘学报,2014,43(5):452-457.
[28] CORPORATION A.NAVSTAR GPS Space Segment/Navigation User Interfaces (Public Release Version)[J].European Journal of Theology,1991,24(5):272.
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