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Chinese Journal of Aeronautics 2012年第4期25卷 631-639页

作者： TU Jia gu defeng WU Yi YI Dongyun College of Science National University of Defense TechnologyChangsha 410073China

In-flight phase center systematic errors of global positioning system（GPS） receiver antenna are the main restriction for improving the precision of precise orbit determination using dual-frequency *** approach is one of the valid methods for in-flight calibration of GPS receiver antenna phase center variations（PCVs） from ground *** this paper,followed by the correction model of spaceborne GPS receiver antenna phase center,ionosphere-free PCVs can be directly estimated by ionosphere-free carrier phase post-fit residuals of reduced dynamic orbit *** the data processing of gravity recovery and climate experiment（GRACE） satellites,the following conclusions are ***,the distributions of ionosphere-free carrier phase post-fit residuals from different periods have the similar systematic ***,simulations show that the influence of phase residual estimations for ionosphere-free PCVs on orbit determination can reach the centimeter ***,it is shown by in-flight data processing that phase residual estimations of current period could not only be used for the calibration for GPS receiver antenna phase center of foretime and current period,but also be used for the forecast of ionosphere-free PCVs in future period,and the accuracy of orbit determination can be well improved.

关键词： global positioning system precise orbit determination phase center variations phase residual estimation GRACE

Integrating BDS and GPS for precise relative orbit determination of LEO formation flying

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Chinese Journal of Aeronautics 2018年第10期31卷 2013-2022页

作者： Bin YI defeng gu Xiao CHANG Kai SHAO College of Liberal Arts and Sciences National University of Defense Technology

Low-Earth-Orbit（LEO） formation-flying satellites have been widely applied in many kinds of space geodesy. Precise Relative Orbit Determination（PROD） is an essential prerequisite for the LEO formation-flying satellites to complete their mission in space. The contribution of the BeiDou Navigation Satellite System（BDS） to the accuracy and reliability of PROD of LEO formation-flying satellites based on a Global Positioning System（GPS） is studied using a simulation method. Firstly, when BDS is added to GPS, the mean number of visible satellites increases from9.71 to 21.58. Secondly, the results show that the 3-Dimensional（3 D） accuracy of PROD, based on BDS-only, GPS-only and BDS ＋ GPS, is 0.74 mm, 0.66 mm and 0.52 mm, respectively. When BDS co-works with GPS, the accuracy increases by 29.73%. Geostationary-Earth-Orbit（GEO） satellites and Inclined Geosynchronous-Orbit（IGSO） satellites are only distributed over the Asia-Pacific region; however, they could provide a global improvement to PROD. The difference in PROD results between the Asia-Pacific region and the non-Asia-Pacific region is not apparent. Furthermore, the value of the Ambiguity Dilution Of Precision（ADOP）, based on BDS ＋ GPS, decreases by 7.50% and 8.26%, respectively, compared with BDS-only and GPS-only. Finally, if the relative position between satellites is only a few kilometres, the effect of ephemeris errors on PROD could be ignored. However, for a several-hundred-kilometre separation of the LEO satellites, the SingleDifference（SD） ephemeris errors of GEO satellites would be on the order of centimetres. The experimental results show that when IGSO satellites and Medium-Earth-Orbit（MEO） satellites co-work with GEO satellites, the accuracy decreases by 17.02%.

关键词： Ambiguity Dilution Of Precision BeiDou Navigation Satellite System Geostationary-Earth-Orbit Global Positioning System LEO formation flying Precise Relative Orbit Determination

Enhanced baseline determination for formation flying LEOs by relative corrections of phase center and code residual variations

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Chinese Journal of Aeronautics 2022年第2期35卷 185-194页

作者： Bin YI defeng gu Bing JU Kai SHAO Houzhe ZHANG College of Liberal Arts and Sciences National University of Defense TechnologyChangsha 410073China TianQin Research Center for Gravitational Physics and School of Physics and Astronomy Sun Yat-sen University(Zhuhai Campus)Zhuhai 519082China National Key Laboratory of Science and Technology on Aerospace Flight Dynamics Beijing Aerospace Control CenterBeijing 100094China

Formation flying Low Earth Orbiters(LEOs)are important for implementing new and advanced concepts in Earth observation *** Baseline Determination(PBD)is a prerequisite for LEOs to complete specified mission *** is usually performed based on space-borne GNSS data,the relative corrections of phase center and code residual variations play crucial roles in achieving the best relative orbit ***,the influences of antenna Relative Phase Centre Variations(RPCVs)and Single-Difference(SD)Melbourne-Wu¨bbena(MW)Combination Residuals Variations(SD MWVs)on PBD are *** methods were tested using flight data from Gravity Recovery And Climate Experiment(GRACE)and GRACE Follow-On(GRACE-FO).Results showed that the maximum values for RPCVs and SD MWVs were 14 mm and 0.32 cycles,***,the RPCVs correction significantly enhanced the baseline accuracy;the K-Band Ranging(KBR)measurement consistency improved by 30.1%and 37.5%for GRACE and GRACE-FO,*** application of SD MWVs further improved the accuracy and reliability of PBD *** GRACE,the ambiguities fixing success rate increased from 85.1%to 97.9%and a baseline consistency of 0.57 mm was achieved for the KBR *** was found that the correction of both RPCVs and SD MWVs reduced the carrier phase observation minus computation residuals from double-difference ionosphere-free *** addition,in-flight data processing demonstrated that RPCVs and SD MWVs estimations for the current period could be used for the previous and subsequent periods.

关键词： Ambiguity resolution Formation flying Precise baseline determination(PBD) Relative phase centre variations(RPCVs)estimation SD MW combination residuals variations(SD MWVs)estimation

Precession–nutation correction for star tracker attitude measurement of STECE satellite

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Chinese Journal of Aeronautics 2014年第1期27卷 117-124页

作者： Lai Yuwang Liu Junhong Ding Yonghe gu defeng Yi Dongyun Department of Mathematics and Systems Science National University of Defense Technology Beijing Institute of Tracking and Telecommunication Technology

Space Technology Experiment and Climate Exploration （STECE） is a small satellite mis- sion of China for space technology experiment and climate exploration. A new test star tracker and one ASTRO 10 star tracker have been loaded on the STECE satellite to test the new star tracker＇s measurement performance. However, there is no autonomous precession nutation correction func- tion for the test star tracker, which causes an apparent periodic deflection in the inter-boresight angle between the two star trackers with respect to each other of up to - 500 arcsec, so the preces- sion and nutation effect needs to be considered while assessing the test star tracker. This paper researches on the precession-nutation correction for the test star traeker＇s attitude measurement and presents a precession-nutation correction method based on attitude quaternion data. The peri- odic deflection of the inter-boresight angle between the two star trackers has been greatly eliminated after the precession and nutation of the test star tracker＇s attitude data have been corrected by the proposed method and the validity of the proposed algorithm has been demonstrated. The in-flight accuracy of the test star tracker has been assessed like attitude noise and low-frequency errors after the precession-nutation correction.

关键词： Attitude determination Low-frequency periodicerror Precession-nutation Star trackers STECE satellite

Spaceborne GPS receiver antenna phase center offset and variation estimation for the Shiyan 3 satellite

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Chinese Journal of Aeronautics 2016年第5期29卷 1335-1344页

作者： gu defeng Lai Yuwang Liu Junhong Ju Bing Tu Jia College of Sciences National University of Defense Technology

In determining the orbits of low Earth orbit （LEO） satellites using spaceborne GPS, the errors caused by receiver antenna phase center offset （PCO） and phase center variations （PCVs） are gradually becoming a major limiting factor for continued improvements to accuracy. Shiyan 3, a small satellite mission for space technology experimentation and climate exploration, was developed by China and launched on November 5, 2008. The dual-frequency GPS receiver payload delivers 1 Hz data and provides the basis for precise orbit determination within the range of a few centimeters. The antenna PCO and PCV error characteristics and the principles influencing orbit determination are analyzed. The feasibility of PCO and PCV estimation and compensation in different directions is demonstrated through simulation and in-flight tests. The values of receiver antenna PCO and PCVs for Gravity Recovery and Climate Experiment （GRACE） and Shiyan 3 satellites are estimated from one month of data. A large and stable antenna PCO error, reaching up to 10.34 cm in the z-direction, is found with the Shiyan 3 satellite. The PCVs on the Shiyan 3 satellite are estimated and reach up to 3.0 cm, which is slightly larger than that of GRACE satellites. Orbit validation clearly improved with independent k-band ranging （KBR） and satellite laser ranging （SLR） measurements. For GRACE satellites, the average root mean square （RMS） of KBR residuals improved from 1.01 cm to 0.88 cm. For the Shiyan 3 satellite, the average RMS of SLR residuals improved from 4.95 cm to 4.06 cm.

关键词： GRACE Phase center offset Phase center variations Shiyan 3 Spaceborne GPS

Basic performance of BeiDou-2 navigation satellite system used in LEO satellites precise orbit determination

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Chinese Journal of Aeronautics 2014年第5期27卷 1251-1258页

作者： Liu Junhong gu defeng Ju Bing Yao Jing Duan Xiaojun Yi Dongyun College of Science National University of Defense Technology

The visibility for low earth orbit（LEO） satellites provided by the BeiDou-2 system is analyzed and compared with the global positioning system（GPS）. In addition, the spaceborne receivers＇ observations are simulated by the BeiDou satellites broadcast ephemeris and LEO satellites orbits. The precise orbit determination（POD） results show that the along-track component accuracy is much better over the service area than the non-service area, while the accuracy of the other two directions keeps at the same level over different areas. However, the 3-dimensional（3D） accuracy over the two areas shows almost no difference. Only taking into consideration the observation noise and navigation satellite ephemeris errors, the 3D accuracy of the POD is about30 cm. As for the precise relative orbit determination（PROD）, the 3D accuracy is much better over the eastern hemisphere than that of the western hemisphere. The baseline length accuracy is 3.4 mm over the service area, and it is still better than 1 cm over the non-service area. This paper demonstrates that the BeiDou regional constellation could provide global service to LEO satellites for the POD and the PROD. Finally, the benefit of geostationary earth orbit（GEO） satellites is illustrated for POD.

关键词： BeiDou-2 Geostationary earth orbit satellites Global positioning system Low earth orbit satellites Precise orbit determination Precise relative orbit determination

Precise orbit determination for TH02-02 satellites based on BDS3 and GPS observations

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Chinese Journal of Aeronautics 2023年第5期36卷 475-485页

作者： Houzhe ZHANG Bing JU defeng gu Ying LIU Kai SHAO Xiaojun DUAN Zhiyong HUANG College of Science National University of Defense TechnologyChangsha 410073China National Key Laboratory of Science and Technology on Aerospace Flight Dynamics Beijing Aerospace Control CenterBeijing 100094China MOE Key Laboratory of TianQin Mission TianQin Research Center for Gravitational PhysicsFrontiers Science Center for TianQinCNSA Research Center for Gravitational WavesSun Yat-sen University(Zhuhai Campus)Zhuhai 519082China School of Artificial Intelligence Sun Yat-sen University(Zhuhai Campus)Zhuhai 519082China School of Physics and Astronomy Sun Yat-sen University(Zhuhai Campus)Zhuhai 519082China Information Engineering University Zhengzhou 450001China

The Tianhui-202(TH02-02)satellite formation,as a supplement to the microwave mapping satellite system Tianhui-201(TH02-01),is the first Interferometric Synthetic Aperture Radar(InSAR)satellite formation-flying system that supports the tracking of BeiDou global navigation Satellite system(BDS3)new B1C and B2a ***,the twin TH02-02 satellites also support the tracking of Global Positioning System(GPS)L1&L2 and BDS B1I&B3I *** the spaceborne receiver employs two independent boards to track the Global Navigation Satellite System(GNSS)satellites,we design an orbit determination strategy by estimating independent receiver clock offsets epoch by epoch for each GNSS to realize the multi-GNSS data fusion from different *** performance of the spaceborne receiver is evaluated and the contribution of BDS3 to the kinematic and reduced-dynamic Precise Orbit Determination(POD)of TH02-02 satellites is *** tracking data onboard shows that the average number of available BDS3 and GPS satellites are 8.7 and 9.1,*** carrier-to-noise ratio and carrier phase noise of BDS3 B1C and B2a signals are comparable to those of ***,strong azimuth-related systematic biases are recognized in the pseudorange multipath errors of B1C and *** pseudorange noise of BDS3 signals is better than that of GPS after eliminating the multipath errors from specific *** the GPS-based reduced-dynamic orbit with single-receiver ambiguity fixing technique as a reference,the results of BDS3-only and BDS3+GPS combined POD are *** Root Mean Square(RMS)of orbit comparison of BDS3-based kinematic and reduced-dynamic POD with reference orbit are better than 7 cm and 3 cm in three-Dimensional direction(3D).The POD performance based on B1C&B2a data is comparable to that based on B1I&*** precision of BDS3+GPS combined kinematic orbit can reach up to 3 cm(3D RMS),which has a more than 25%improvement relative to the GPS-only *** addi

关键词： BDS3 Multi-GNSS Precise orbit determination Spaceborne GNSS receiver TH02-02

Reduced Dynamic Orbit Determination Using Differenced Phase in Adjacent Epochs for Spaceborne Dual-frequency GPS

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Chinese Journal of Aeronautics 2011年第6期24卷 789-796页

作者： gu defeng YI Dongyun State Key Laboratory of Astronautic Dynamics Xi ＇an 710043 China College of Sciences National University of Defense Technology Changsha 410073 China

We study on reduced dynamic orbit determination using differenced phase in adjacent epochs for spacebome dual-frequency GPS. This method not only overcomes the shortcomings that the epoch-difference kinematic method cannot be used when observation geometry is poor or observations are insufficient, but also avoids solving the ambiguity in the zero-difference reduced dynamic method. As the epoch-difference method is not sensitive to the impact of phase cycle slips, it can lower the difficulty of slip detection in phase observation preprocessing. In the solution strategies, we solve the high-dimensional matrix computation problems by decomposing the long observation arc into a number of short arcs. By gravity recovery and climate experiment （GRACE） satellite orbit determination and compared with GeoForschungsZentrum （GFZ） post science orbit, for epoch-difference reduced dynamic method, the root mean squares （RMSs） of radial, transverse and normal components are 1.92 cm, 3.83 cm and 3.80 cm, and the RMS in three dimensions is 5.76 cm. The solution＇s accuracy is comparable to the zero-difference reduced dynamic method.

关键词： dual-frequency GPS phase difference in adjacent epochs satellite reduced dynamic orbit determination

Quality analysis of multi-GNSS observation data based on iGMAS

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Quality analysis of multi-GNSS observation data based on iGM...

多机构比对融合的分布式InSAR编队星间基线确定

第十一届中国卫星导航年会

作者： Houzhe Zhang Kai Shao defeng gu Xiaojun Duan College of Liberal Arts and Sciences National Univeristy of Defence and Technology School of Physics and Astronomy Sun Yat-Sen University(Zhuhai Campus)

The quality of GNSS(Global Navigation Satellite System) observation data is the primary factor affecting the accuracy of navigation satellite orbit determination, and it is an important reference for

关键词： BDS/GPS/Galileo/GLONASS quality analysis carrier to noise ratio multipath errors carrier phase noise inter system bias

来源： cnki会议 cnki会议 cnki会议评论

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航空学报 2018年第1期39卷 238-247页

作者：易彬秦显平谷德峰鞠冰国防科技大学文理学院长沙410073 西安测绘研究所西安710054

星间基线高精度确定是分布式干涉合成孔径雷达(InSAR)系统完成科学任务的重要保证,受星载全球定位系统(GPS)接收机连续跟踪弧段短、个别弧段共视GPS卫星个数少或模糊度固定成功率低、频繁轨道机动等因素影响,分布式InSAR高精度基线确定... 详细信息

星间基线高精度确定是分布式干涉合成孔径雷达(InSAR)系统完成科学任务的重要保证,受星载全球定位系统(GPS)接收机连续跟踪弧段短、个别弧段共视GPS卫星个数少或模糊度固定成功率低、频繁轨道机动等因素影响,分布式InSAR高精度基线确定仍有不可靠的风险。通过多机构产品互比来识别基线精度较差的时间段,降低不可靠风险,并通过多机构产品融合进一步提高基线精度。选用重力反演与气候实验(GRACE)卫星数据进行实验,国防科技大学(NDT)和西安测绘研究所(CHS)采用不同的基线处理软件和简化动力学策略,保证了各自的基线产品具有一定的独立性。实验表明,多机构互比对可以有效识别基线精度较差的时间段,NDT和CHS的基线产品之间具有很好的一致性,互比对残差的均方根(RMS)在R、T、N方向分别为0.7、0.9、0.7mm,二者之间没发现明显系统偏差,大约97.86%的基线三维互比对残差量级在2mm以内。两个机构基线产品融合后发现可进一步降低基线产品中的随机波动误差,K/Ka波段测距(KBR)系统校核结果表明融合基线产品精度较NDT基线产品提高8.97%,较CHS基线产品提高29.21%。

关键词：分布式InSAR 航天器编队飞行基线确定多机构融合