伪随机脉冲先验值对低轨卫星简化动力学定轨精度的影响
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摘要
低轨卫星简化动力学定轨中引入伪随机脉冲可有效提高定轨精度,但伪随机脉冲先验值(时间间隔、先验标准差)会影响伪随机脉冲估值大小,进而影响定轨精度。基于GRACE(Gravity Recovery and Climate Experiment)卫星轨道分析伪随机脉冲先验值对单天解简化动力学定轨精度的影响,实验表明,时间间隔从240min减至6min,先验标准差从1×10~(-4) mm/s增至1×10~(-1) mm/s,伪随机脉冲总的估值大小由1×10~(-2)mm/s增至1×101 mm/s,定轨精度从几十cm提高到2cm;当先验标准差大于1×10~(-1) mm/s,继续增加先验标准差,伪随机脉冲估值不变,定轨精度不再提高。因此,对于单天解轨道,时间间隔减小至6min,先验标准差增至1×10~(-1) mm/s,伪随机脉冲估值增大,定轨精度提高;继续增大先验标准差,伪随机脉冲估值不变,定轨精度不再提高。利用不同高度的Swarm卫星验证了该结论的有效性。
Pseudo-stochastic pulses can improve the accuracy of LEO reduced-dynamic orbit determination effectively,but the pseudo-stochastic pulse priors(i.e.,time interval and a priori sigma)will affect the values of pseudo-stochastic pulse,thereby affecting orbit accuracy.In this paper,single-day GRACE orbit experiments based on reduced-dynamic method show that time interval decreases from 240 min to 6 min,apriori sigma increases from 1×10~(-4) mm/s to 1×10~(-1) mm/s,the total values of pseudo-stochastic pulse increases from 1×10~(-2) mm/s to 1×101 mm/s,and the orbit accuracy improves from tens of centimeters to 2 cm;when a priori sigma is greater than 1×10~(-1) mm/s,apriorisigma continues to increase,the values of pseudo-stochastic pulse remain unchanged and the orbit accuracy unimproved.Therefore,for single-day orbit solution,time interval is reduced to 6 min,a priori sigma goes up to 1×10~(-1) mm/s,the values of pseudo-stochastic pulse increases,the orbit accuracy improves;apriori sigma continued to increase,the values of pseudo-stochastic pulse keep unchanged,and the orbit accuracy is unimproved.Using Swarm orbit experiments of different heights can be used to verify the validation of the conclusion.
Pseudo-stochastic pulses can improve the accuracy of LEO reduced-dynamic orbit determination effectively,but the pseudo-stochastic pulse priors(i.e.,time interval and a priori sigma)will affect the values of pseudo-stochastic pulse,thereby affecting orbit accuracy.In this paper,single-day GRACE orbit experiments based on reduced-dynamic method show that time interval decreases from 240 min to 6 min,apriori sigma increases from 1×10~(-4) mm/s to 1×10~(-1) mm/s,the total values of pseudo-stochastic pulse increases from 1×10~(-2) mm/s to 1×101 mm/s,and the orbit accuracy improves from tens of centimeters to 2 cm;when a priori sigma is greater than 1×10~(-1) mm/s,apriorisigma continues to increase,the values of pseudo-stochastic pulse remain unchanged and the orbit accuracy unimproved.Therefore,for single-day orbit solution,time interval is reduced to 6 min,a priori sigma goes up to 1×10~(-1) mm/s,the values of pseudo-stochastic pulse increases,the orbit accuracy improves;apriori sigma continued to increase,the values of pseudo-stochastic pulse keep unchanged,and the orbit accuracy is unimproved.Using Swarm orbit experiments of different heights can be used to verify the validation of the conclusion.
引文
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[23]Guo Jing,Zhao Qile,Li Min,et al.Centimeter Level Orbit Determination for HY2A Using GPS Data[J].Geomatics and Information Science of Wuhan University,2013,38(1):52-55(郭靖,赵齐乐,李敏,等.利用星载GPS观测数据确定海洋2A卫星cm级精密轨道[J].武汉大学学报·信息科学版,2013,38(1):52-55
[24]Jaggi A,Beutler G,Hugentobler U.Efficient Stochastic Orbit Modeling Techniques Using Least Squares Estimators[M]//A Window on the Future of Geodesy.Berlin:Springer,2004
[25]Bertiger W,Bar-Sever Y,Desai S,et al.GRACE:Millimeters and Microns in Orbit[C].ION GPS,Poland,2002
[26]van den Ijssel J,Encarna92o J,Doornbos E,et al.Precise Science Orbits for the Swarm Satellite Constellation[J].Adv Space Res,2015,56(6):1 042-1 055
[2]Tapley B D,Bettadpur S,Watkins M,et al.The Gravity Recovery and Climate Experiment:Mission Overview and Early Results[J].Geophys Res Lett,2004,31(9):L09607
[3]Drinkwater M,Haagmans R,Muzi D,et al.The GOCE Gravity Mission:ESA’s First Core Explorer[C].3rd GOCE User Workshop,Frascati,Italy,2006
[4]Macmillan S,Olsen N.Observatory Data and the Swarm Mission[J].Earth,Planets and Space,2013,65:1 355-1 362
[5]Wang Zhengtao,Chao Nengfang.Time-Variable Gravity Signal in Greenland Revealed by Swarm High-Low Satellite-to-Satellite Tracking[J].Chinese J Geophys,2014,57(10):3 117-3 128(王正涛,超能芳.利用Swarm卫星高低跟踪探测格林兰岛时变重力信号[J].地球物理学报,2014,57(10):3 117-3 128)
[6]Flechtner F,Morton P,Watkins M,et al.Status of the GRACE Follow-on Mission,Gravity Geoid and Height Systems[C]//International Association of Geodesy Symposia.Berlin:Springer International Publishing,2014
[7]Chen Junyong.Recent Development in the Earth Gravity Field Determination by Modern LEO Satellite[J].Science of Surveying and Mapping,2002,27(1):8-10(陈俊勇.现代低轨卫星对地球重力场探测的实践和进展[J].测绘科学,2002,27(1):8-10)
[8]Visser P,van den Ijssel J.Aiming at a 1-cm Orbit for Low Earth Orbiters:Reduced-Dynamical and Kinematic Precise Orbit Determination[J].Space Sci Rev,2003,10(8):27-36
[9]Jggi A,Hugentobler U,Beutler G.Pseudo-Stochastic Orbit Modeling Techniques for Low-Earth Orbiters[J].J Geod,2006,80(1):47-60
[10]Svehla D,Rothacher M.Kinematic and Reduced Dynamic Precise Orbit Determination of Low Earth Orbiters[J].Advances in Geosciences,2002,1(1):47-56
[11]Yunck T P,Wu S C,Bertiger W I,et al.First Assessment of GPS-Based Reduced Dynamic Orbiter Determination on TOPEX/POSEIDON[J].Geophysics Research Letter,1994,21(7):541-544
[12]Beutler G,Jggi A,Hugentobler U,et al.Efficient Satellite Orbit Modeling Using Pseudo-Stochastic Parameters[J].J Geod,2006,80(7):353-372
[13]van den Ijssel J,Visser P,Pati1o R.CHAMP Precise Orbit Determination Using GPS Data[J].Adv Space Res,2003,31(8):1 889-1 895
[14]Haines B,Bar-Sever Y,Bertiger W,et al.OneCentimeter Orbit Determination for Jason-1:New GPS-Based Strategies[J].Mar Geod,2004,27(1-2):299-318
[15]Jggi A,Hugentobler U,Bock H,et al.Precise Orbit Determination for GRACE Using Undifferenced or Doubly Differenced GPS Data[J].Adv Space Res,2007,39(10):1 612-1 619
[16]Hwang C,Tseng T P,Lin T,et al.Precise Orbit Determination for the FORMOSAT-3/COSMIC Satellite Mission Using GPS[J].J Geod,2008,83(5):477-489
[17]Bock H,Jggi A,Beutler G,et al.GOCE:Precise Orbit Determination for the Entire Mission[J].J Geod,2014,88(11):1 047-1 060
[18]van den Ijssel J,Encarna92o J A,Doornbos E,et al.Precise Science Orbits for the Swarm Satellite Constellation[J].Adv Space Res,2015,56(6):1 042-1 055
[19]Han Baomin,Zhu Xiuying,Liu Lintao,et al.Estimation of Pseudo-Stochastic Pulses and Their Application in Reduced-Dynamic Orbit Determination[J].Geomatics and Information Science of Wuhan University,2007,27(1):466-469(韩保民,朱秀英,柳林涛,等.伪随机脉冲估计及其在简化动力学定轨中的应用[J].武汉大学学报·信息科学版,2007,27(1):466-469)
[20]Zhao Chunmei,Cheng Pengfei,Yi Pengju.Reduced-Dynamic Satellite Orbit Determination Based on Pseudo-Stochastic Pulse Estimation[J].Journal of Astronautics,2011,32(4):762-766(赵春梅,程鹏飞,益鹏举.基于伪随机脉冲估计的简化动力学卫星定轨方法[J].宇航学报,2011,32(4):762-766)
[21]Liu Weiping,Hao Jinming,Tian Yingguo,et al.Fast Parameter Estimation for Pseudo-Stochastic Pulse[J].Geomatics and Information Science of Wuhan University,2015,40(11):1 487-1 492(刘伟平,郝金明,田英国,等.一种伪随机脉冲的快速参数估计方法[J].武汉大学学报·信息科学版,2015,40(11):1 487-1 492)
[22]Qin Jian,Guo Jinyun,Kong Qiaoli,et al.Precise Orbit Determination of Jason-2 with Precision of Centimeters Based on Satellite-Borne GPS Technique[J].Geomatics and Information Science of Wuhan University,2014,39(2):137-141(秦建,郭金运,孔巧丽,等.Jason-2卫星星载GPS数据cm级精密定轨[J].武汉大学学报·信息科学版,2014,39(2):137-141)
[23]Guo Jing,Zhao Qile,Li Min,et al.Centimeter Level Orbit Determination for HY2A Using GPS Data[J].Geomatics and Information Science of Wuhan University,2013,38(1):52-55(郭靖,赵齐乐,李敏,等.利用星载GPS观测数据确定海洋2A卫星cm级精密轨道[J].武汉大学学报·信息科学版,2013,38(1):52-55
[24]Jaggi A,Beutler G,Hugentobler U.Efficient Stochastic Orbit Modeling Techniques Using Least Squares Estimators[M]//A Window on the Future of Geodesy.Berlin:Springer,2004
[25]Bertiger W,Bar-Sever Y,Desai S,et al.GRACE:Millimeters and Microns in Orbit[C].ION GPS,Poland,2002
[26]van den Ijssel J,Encarna92o J,Doornbos E,et al.Precise Science Orbits for the Swarm Satellite Constellation[J].Adv Space Res,2015,56(6):1 042-1 055