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| 1 | Orbit determination and time synchronization for a GEO/IGSO satellite navigation constellation with regional tracking network显示文摘Aiming at regional services,the space segment of COMPASS (Phase I) satellite navigation system is a constellation of Geostationary Earth Orbit (GEO),Inclined Geostationary Earth Orbit (IGSO) and Medium Earth Orbit (MEO) satellites.Precise orbit determination (POD) for the satellites is limited by the geographic distribution of regional tracking stations.Independent time synchronization (TS) system is developed to supplement the regional tracking network,and satellite clock errors and orbit data may be obtained by simultaneously processing both tracking data and TS data.Consequently,inconsistency between tracking system and TS system caused by remaining instrumental errors not calibrated may decrease navigation accuracy.On the other hand,POD for the mixed constellation of GEO/IGSO/MEO with the regional tracking network leads to parameter estimations that are highly correlated.Notorious example of correlation is found between GEO's orbital elements and its clock errors.We estimate orbital elements and clock errors for a 3GEO+2IGSO constellation in this study using a multi-satellite precise orbit determination (MPOD) strategy,with which clock error elimination algorithm is applied to separate orbital and clock estimates to improve numerical efficiency.Satellite Laser Ranging (SLR) data are used to evaluate User Ranging Error (URE),which is the orbital error projected on a receiver's line-of-sight direction.Two-way radio-wave time transfer measurements are used to evaluate clock errors.Experimenting with data from the regional tracking network,we conclude that the fitting of code data is better than 1 m in terms of Root-Mean-Square (RMS),and fitting of carrier phase is better than 1 cm.For orbital evaluation,difference between computed receiver-satellite ranging based on estimated orbits and SLR measurements is better than 1 m (RMS).For clock estimates evaluation,2-hour linear-fitting shows that the satellite clock rates are about 1.E-10 s/s,while receiver clock rates are about 1×10 13-1×10 12 s/s.For the 72-hour POD experiment,the average differences between POD satellite clock rates estimates and clock measurements based on TS system are about 1×10 13 s/s,and for receiver clock rates,the differences are about 1×10 15 s/s. | ZHOU ShanShi HU XiaoGong WU Bin LIU Li QU WeiJing GUO Rui HE Feng CAO YueLing Wu XiaoLi ZHU LingFeng SHI Xin TAN HongLi | 2011 | Science China(Physics,Mechanics & Astronomy)2011，54，6： | 44 |
| 2 | 利用星间双向测距数据进行北斗卫星集中式自主定轨的初步结果分析显示文摘自主定轨是导航卫星自主导航的重要任务,是指在地面运行控制系统不可用的情形下,利用星间测距维持导航系统星历的自主更新.本文利用北斗新一代导航试验卫星搭载的Ka波段星间双向测距数据,进行集中式自主定轨试验.首先给出了星间双向测距数据的处理流程和数学模型,并分析了星间双向测距数据的测量特性.结果表明星间双向测距数据是一种高精度的距离测量.将星间双向测距数据用于定轨处理,残差标准差小于1 0 cm,均值好于1.0 cm,解算的设备零值稳定度好于0.2 ns.分别利用重叠弧段比较、用户等效距离误差评估和激光残差等方式评估了自主定轨的精度.结果表明,在一个地面锚固站支持下,自主定轨得到的卫星轨道径向重叠弧段互差优于6 cm,预报2 4 h径向重叠弧段互差优于1 0 cm.2 4 h预报轨道用户等效距离误差为0.4 3 m,优于L波段预报轨道的0.76 m,激光残差优于1 0 cm.星间链路对地观测为自主定轨提供空间基准,避免星座的整体旋转.本文讨论对地测量时长对自主定轨的影响.结果表明即使星间链路对地观测的截止高度角为60°,自主定轨结果和2 4 h预报轨道径向误差优于10 cm,三维位置优于1.5 m. | 唐成盼 胡小工 周善石 潘军洋 郭睿 胡光明 朱陵凤 李晓杰 吴杉 王琰 | 2017 | 中国科学:物理学、力学、天文学2017，47，2： | 26 |
| 3 | 北斗三号卫星两种定轨模式精度比较分析显示文摘北斗全球卫星导航系统(BDS-3)已经于2018年年底建成基本系统,并计划于2020年建成完整系统,而精确的卫星轨道是实现高性能全球服务的前提。本文基于北斗三号基本系统的18颗中圆轨道(MEO)卫星,评估了北斗三号卫星星间链路的测量噪声与测距精度,利用中国境内12个区域监测站的星地观测和星间链路观测,进行了联合卫星轨道测定试验,并与单纯区域监测站观测定轨结果进行了比较,分析了两种定轨模式重叠弧段轨道误差、轨道预报精度和激光检核精度。结果表明:北斗三号卫星的星间链路测量噪声为2.9cm,测距精度约为4.4cm;仅采用区域测站定轨,重叠弧段三维位置误差RMS为66.7cm,加入星间链路后可降低至15.4cm,提高了76.9%,24h轨道预报位置精度也由114.1cm提升至20.3cm,提升了83.2%,激光检核径向精度为8.4cm左右,明显优于北斗二号卫星轨道精度。 | 杨宇飞 杨元喜 胡小工 唐成盼 赵立谦 徐君毅 | 2019 | 测绘学报2019，48，7： | 26 |
| 4 | Improvement of orbit determination for geostationary satellites with VLBI tracking显示文摘China’s COMPASS satellite navigation system consists of five or more geostationary (GEO) satellites.The roles of GEO satellites are to improve the regional user’s positioning accuracy and provide the continuous Radio Determination Satellite Service.The motion of GEO satellites relative to a ground tracking station is almost fixed,and regular orbit maneuvers are necessary to maintain the satellites’ allocated positions above the equator.These features present difficulties in precise orbit determination (POD).C-band ranging via onboard transponders and the L-band pseudo-ranging technique have been used in the COMPASS system.This paper introduces VLBI tracking,which has been successfully employed in the Chinese lunar exploration programs Chang’E-1 and Chang’E-2,to the POD of GEO satellites.In contrast to ranging,which measures distances between a GEO satellite and an observer,VLBI is an angular measurement technique that constrains the satellite’s position errors perpendicular to the satellite-to-observer direction.As a demonstration,the Chinese VLBI Network organized a tracking and orbit-determination experiment for a GEO navigation satellite lasting 24 h.This paper uses the VLBI delay and delay-rate data,in combination with C-band ranging data,to determine the GEO satellite’s orbit.The accuracies of the VLBI delay and delay rate data are about 3.6 ns and 0.4 ps/s,respectively.Data analysis shows that the VLBI data are able to calibrate systematic errors of the C-band ranging data,and the combination of the two observations improves orbit prediction accuracy with short-arc data,which is important for orbital recovery after maneuvers of GEO satellites.With the implementation of VLBI2010,it is possible for VLBI to be applied in the COMPASS satellite navigation system. | HUANG Yong HU XiaoGong ZHANG XiuZhong JIANG DongRong GUO Rui WANG Hong SHI ShanBin | 2011 | Chinese Science Bulletin2011，56，26： | 18 |
| 5 | Orbit determination and prediction accuracy analysis for a regional tracking network显示文摘China's COMPASS satellite navigation system relies on a regional tracking network to provide navigation services. Limited by its geographic border,the regional network is able to cover only 30% of the medium-earth-orbits(MEO). Accuracy of determined and predicted orbits is not able to satisfy system requirements if the tracking data processing strategy for global tracking network processing is used for the regional network. Two major error sources for orbital prediction are accuracy of initial orbital elements and dynamical modeling. To achieve better prediction accuracy,we propose a two-step orbit determination and prediction strategy. For step 1,only solar radiation pressure(SRP) parameters are estimated along with the orbital elements and other parameters; for step 2,all parameters are estimated but the SRP parameters are tightly constrained to their step 1 estimates. Experimenting with data from a regional GPS network,we conclude for orbital prediction using the proposed two-step strategy,the average user range error(URE) for 24-h prediction arcs is better than 0.6 m. | ZHOU ShanShi 1,2,3 ,HU XiaoGong 1 & WU Bin 1 1 Shanghai Astronomical Observatory,Chinese Academy of Sciences,Shanghai 200030,China 2 Graduate University of Chinese Academy of Sciences,Beijing 100049,China 3 Research Center of GNSS,Wuhan 430079,China | 2010 | Science China(Physics,Mechanics & Astronomy)2010，53，6： | 16 |
| 6 | Mars Express tracking and orbit determination trials with Chinese VLBI network显示文摘With strong support from European Space Agency (ESA),Shanghai Astronomical Observatory (SHAO) organized a tracking and orbit determination trails using Chinese VLBI Network (CVN) to track Mars Express,the first Mars probe launched by ESA. Using a high-resolution VLBI software correlator and Doppler measurement system developed in-house,two sets of tracking data,VLBI and Doppler,were acquired. The trials represent the first successful foray held in China to track a probe about 360 million kilometers away from the Earth. The tracking data are analyzed using a Mars satellite orbit determination software system developed at SHAO. The results show that the accuracy of 5 s integrated three-way-Doppler data is about 0.3 mm/s,or roughly the same accuracy as ESA's tracking data. Position discrepancies between the Doppler-based orbit solution of 8 h arc-length (about 1 orbital revolution) and ESA's reconstructed orbit are of the order of several hundred meters. In preparing for the Russia-China co-sponsored Mars exploration mission Phobos-Grunt-YingHuo,simulations were carried out to evaluate the achievable orbital accuracy levels and the contributions of VLBI and Doppler data respectively. Results show that Doppler data provide better orbit accuracy,so that for VLBI to be able to provide kilometer level orbit solutions,the accuracy of VLBI measurement needs to be improved by at least one order of magnitude. | CAO JianFeng HUANG Yong HU XiaoGong MA maoLi ZHENG WeiMin | 2010 | Chinese Science Bulletin2010，55，32： | 14 |
| 7 | Orbit determination for geostationary satellites with the combination of transfer ranging and pseudorange data显示文摘Geostationary satellites(GEOs) play a significant role in the regional satellite navigation system.Simulation experiments show that the clock corrections could be mitigated through a single strategy or double differencing strategies for a navigation constellation,but for the mode of individual GEO orbit determination,high precision orbit and clock correction could not be obtained in the orbit determination based on the pseudorange data.A new GEO combined precise orbit determination(POD) strategy is studied in this paper,which combines pseudorange data and C-band transfer ranging data.This strategy overcomes the deficiency of C-band transfer ranging caused by limited stations and tracking time available.With the combination of transfer ranging and pseudorange data,clock corrections between the GEO and the stations can be estimated simultaneously along with orbital parameters,maintaining self-consistency between the satellite ephemeris and clock correction parameters.The error covariance analysis is conducted to illuminate the contributions from the transfer ranging data and the psudoranging data.Using data collected for a Chinese GEO satellite with 3 C-band transfer ranging stations and 4 L-band pseudorange tracking stations,POD experiments indicate that a meter-level accuracy is achievable.The root-mean-square(RMS) of the post-fit C-band ranging data is about 0.203 m,and the RMS of the post-fit pseudorange is 0.408 m.Radial component errors of the POD experiments are independently evaluated with the satellite laser ranging(SLR) data from a station in Beijing,with the residual RMS of 0.076 m.The SLR evaluation also suggests that for 2-h orbital predication,the predicted radial error is about 0.404 m,and the clock correction error is about 1.38 ns.Even for the combination of one C-band transfer ranging station and 4 pseudorange stations,POD is able to achieve a reasonable accuracy with the radial error of 0.280 m and the 2-h predicted radial error of 0.888 m.Clock synchronization between the GEO and tracking stations is achieved with an estimated accuracy of about 1.55 ns,meeting the navigation service requirements. | GUO Rui1,2,3,4,HU XiaoGong2,4,LIU Li1,WU XiaoLi1,HUANG Yong2,4 & HE Feng1 1 Beijing Global Information Application and Development Center,Beijing 100094,China 2 Shanghai Astronomical Observatory,Chinese Academy of Sciences,Shanghai 200030,China 3 Graduate University of Chinese Academy of Sciences,Beijing 100049,China 4 Space Navigation and Positioning Technology,Laboratory of Shanghai Municipal,Shanghai 200030,China | 2010 | Science China(Physics,Mechanics & Astronomy)2010，53，9： | 13 |
| 8 | 同步卫星无源测轨中的时差定位与精度分析显示文摘多站时差定位是最重要的无源定位方法之一。研究了基于四站时差测量的地球同步卫星无源定位和定轨方法。介绍了四站时差定位的基本原理,给出了四站时差定位算法和详细算法流程,推导了四站时差定位精度的误差传播方程。重点分析了测量精度、布站方式、基线长度、站址误差对同步卫星定位精度的影响。通过MonteCarlo仿真,验证了四站时差定位算法与误差分析结果的一致性。仿真结果表明:测量误差、布站方式、基线长度和站址误差均是定位误差的关键影响因素;布站方式以倒Y型布站效果最佳,菱形或矩形布站方式存在奇异区;为达到km量级定位精度,则基线长度应大于1 000km;采用四站时差测轨时,站址坐标精度水平应优于1m。 | 彭华峰 曹金坤 郑超 | 2012 | 系统工程与电子技术2012，34，11： | 8 |
| 9 | Precise orbit determination of Haiyang-2 using satellite laser ranging显示文摘With the successful launch and official commissioning of China's first dynamic ocean environment satellite Haiyang-2(HY-2),China's capabilities for oceanic environment monitoring and oceanic resource detecting have been further improved and enhanced.Precise tracking and orbit determination are not only key technical concerns in the ocean dynamic environment satellite project but also necessary conditions for carrying out related oceanic science research using observational data obtained using spaceborne instruments including radar altimeter.In this study,the current available status of international satellite laser ranging(SLR) monitoring on HY-2 was introduced.Six-months of SLR data from HY-2 were processed to obtain precise satellite orbit information using the dynamic orbit determination method.We carried out a detailed assessment of the SLR orbit accuracy by internal evaluation,comparisons with the orbit derived by the French Doppler orbitography and radio-positioning integrated by satellite(DORIS) system,and station-satellite distance validation.These assessments indicate that the three-dimensional orbital accuracy of HY-2 is about 12.5 cm,and the radial accuracy is better than 3 cm.It provides a good example of the application of international SLR monitoring and precise orbit determination in China's earth observation satellite project. | ZHAO Gang ZHOU XuHua WU Bin | 2013 | Chinese Science Bulletin2013，58，6： | 8 |
| 10 | Orbit determination and prediction for Beidou GEO satellites at the time of the spring/autumn equinox显示文摘Geostationary(GEO) satellites form an indispensable component of the constellation of Beidou navigation system(BDS). The ephemerides, or predicted orbits of these GEO satellites(GEOs), are broadcast to positioning, navigation, and timing users. User equivalent ranging error(UERE) based on broadcast message is better than 1.5 m(root formal errors: RMS) for GEO satellites. However, monitoring of UERE indicates that the orbital prediction precision is significantly degraded when the Sun is close to the Earth's equatorial plane(or near spring or autumn Equinox). Error source analysis shows that the complicated solar radiation pressure on satellite buses and the simple box-wing model maybe the major contributor to the deterioration of orbital precision. With the aid of BDS' two-way frequency and time transfer between the GEOs and Beidou time(BDT, that is maintained at the master control station), we propose a new orbit determination strategy, namely three-step approach of the multi-satellite precise orbit determination(MPOD). Pseudo-range(carrier phase) data are transformed to geometric range(biased geometric range) data without clock offsets; and reasonable empirical acceleration parameters are estimated along with orbital elements to account for the error in solar radiation pressure modeling. Experiments with Beidou data show that using the proposed approach, the GEOs' UERE when near the autumn Equinox of 2012 can be improved to 1.3 m from 2.5 m(RMS), and the probability of user equivalent range error(UERE)<2.0 m can be improved from 50% to above 85%. | LI XiaoJie ZHOU JianHua HU XiaoGong LIU Li GUO Rui ZHOU ShanShi | 2015 | Science China(Physics,Mechanics & Astronomy)2015，58，8： | 8 |
| 11 | 一种用于同步静止卫星监测的微型VLBI网显示文摘针对地球静止轨道(GEO)卫星全天时全天候高精度的监测需求,考虑传统甚长基线干涉(VLBI)测站高成本、高投入和GEO卫星专用观测时段有限等制约条件,研发了简易型VLBI观测系统,并组建了包括上海、都匀和乌鲁木齐三站的微型VLBI网(micro VLBI network,MVN),开展了并置站测试以及对GEO卫星亚太6C的连续监测,并评估了当前MVN的观测能力。结果表明MVN扣除系统差后的单站接收精度为2 ns,各基线观测时延拟后残差约几纳秒,GEO目标实测位置精度为百米级(内外符精度分别约100 m和400 m)。不同于传统VLBI和其他GEO监测手段,MVN还具备全天时、全天候、低造价、易布设及易推广等特点,充分表明了其在GEO卫星监测领域的应用价值。 | 张志斌 王维 杨鹏 KALIUZHNYIMylolay 米立功 李光辉 李鹏 唐正宏 崔朗 黄勇 王广利 | 2020 | 中国空间科学技术2020，40，5： | 5 |
| 12 | 基于北斗卫星校准的连接端站干涉测量与定轨显示文摘为提高连接端站干涉(connected-element interferometry,CEI)测量对地球静止卫星轨道(geostationary satellite orbit,GEO)空间角位置的测量精度,通常采用射电源标校消除大部分公共误差,但需要在测站配置大口径高增益天线以接收射电源的微弱信号。针对该问题,以北斗导航卫星为标校源,仅利用测站现有天线即可实现高精度CEI测量。利用喀什测控站相距20 km的两套天线设备对天链GEO卫星开展CEI测量。经北斗卫星校准后,时延测量精度可达0.03 ns。定轨结果表明,7 h的时延和单站测距数据联合定轨位置精度可达37 m,预报12 h位置偏差约为78 m。与3000 km范围分布的多站测距系统24 h弧段定轨精度相当,验证了该技术用于GEO卫星高精度测定轨和机动后轨道恢复的可行性。 | 樊敏 黄勇 黄磊 陈少伍 李赞 | 2021 | 系统工程与电子技术2021，43，5： | 4 |
| 13 | GEO卫星东西机动监视与移动窗口轨迹拟合显示文摘快速获得可靠的实际机动点火时段,可以有效缩短GEO卫星在整个导航星座中的不可用时段。针对GEO卫星的星下点运动特性,本文提出同步根数加东西漂移加速度的运动参数集,验证了七参数模型对10min窗口轨迹拟合的可行性。基于东西定点机动的工作原理,提出联合半长轴拟合窗口序列和测站测距拟合-预报残差均方根窗口序列的机动监视方法。利用C波段转发测距资料,对某GEO卫星包含变轨弧段在内的1d数据进行开窗运动学拟合分析,验证了机动检测方法的有效性和灵敏性。 | 杜兰 张中凯 李晓杰 王若璞 刘利 郭睿 | 2014 | 测绘学报2014，43，3： | 4 |
| 14 | 不同姿态控制模式下的北斗卫星定轨策略研究显示文摘北斗卫星的姿态控制分为动态偏置、零偏置和连续动偏3种,不同类型卫星、不同姿态控制模式、不同时段下定轨精度不一致,影响了北斗系统的连续性。详细研究了北斗不同类型卫星在不同姿态控制模式下的最优定轨策略,并基于实测数据进行试验,结果表明,BeiDou-2 IGSO(inclined geosynchronous orbit)/MEO(medium earth orbit)卫星采用基于星地钟差约束下多星定轨方法和ECOM(extended CODE model)5参数模型相结合的方法定轨精度最优,零偏期间,用户等效距离误差值为2.08 m,全球激光评估轨道视向精度约为1 m;BeiDou-3 IGSO/MEO卫星采用常规多星定轨和ECOM 5参数模型相结合的方法定轨精度最优;连续动偏期间,用户等效距离误差值为1.22 m,全球激光评估轨道视向精度为0.23 m,与动偏期间精度一致;GEO(geostationary earth orbit)卫星在春秋分附近时段采用基于星地钟差约束下多星定轨方法和ECOM 9参数模型相结合的方法定轨精度最优,用户等效距离误差值为0.72 m。 | 李晓杰 郭睿 吴杉 常志巧 刘帅 陈建兵 | 2019 | 武汉大学学报(信息科学版)2019，44，10： | 3 |
| 15 | Satellite-station time synchronization information based real-time orbit error monitoring and correction of navigation satellite in Beidou System显示文摘Satellite-station two-way time comparison is a typical design in Beidou System(BDS)which is significantly different from other satellite navigation systems.As a type of two-way time comparison method,BDS time synchronization is hardly influenced by satellite orbit error,atmosphere delay,tracking station coordinate error and measurement model error.Meanwhile,single-way time comparison can be realized through the method of Multi-satellite Precision Orbit Determination(MPOD)with pseudo-range and carrier phase of monitor receiver.It is proved in the constellation of 3GEO/2IGSO that the radial orbit error can be reflected in the difference between two-way time comparison and single-way time comparison,and that may lead to a substitute for orbit evaluation by SLR.In this article,the relation between orbit error and difference of two-way and single-way time comparison is illustrated based on the whole constellation of BDS.Considering the all-weather and real-time operation mode of two-way time comparison,the orbit error could be quantifiably monitored in a real-time mode through comparing two-way and single-way time synchronization.In addition,the orbit error can be predicted and corrected in a short time based on its periodic characteristic.It is described in the experiments of GEO and IGSO that the prediction accuracy of space signal can be obviously improved when the prediction orbit error is sent to the users through navigation message,and then the UERE including terminal error can be reduced from 0.1 m to 0.4 m while the average accuracy can be improved more than 27%.Though it is still hard to make accuracy improvement for Precision Orbit Determination(POD)and orbit prediction because of the confined tracking net and the difficulties in dynamic model optimization,in this paper,a practical method for orbit accuracy improvement is proposed based on two-way time comparison which can result in the reflection of orbit error. | HE Feng ZHOU ShanShi HU XiaoGong ZHOU JianHua LIU Li GUO Rui LI XiaoJie WU Shan | 2014 | Science China(Physics,Mechanics & Astronomy)2014，57，7： | 3 |
| 16 | Orbit determination and thrust force modeling for a maneuvered GEO satellite using two-way adaptive Kalman filtering显示文摘A two-way adaptive Kalman filter is proposed by combining a two-way filter with an adaptive filter for orbit determination of a maneuvered GEO satellite.A method of using Newton's high-resolution differential formula and polynomial fitting for modeling the thrust force of a maneuvered GEO satellite is developed.The adaptive factor,which balances the contributions of the measurements and the dynamic model information,is determined by using a two-segment function and predicted residual statistics.Simulations with a maneuvered GEO satellite tracked by the Chinese ground tracking network were conducted to verify the performance of the proposed orbit determination technique and the method of thrust force modeling.The results show that refining the thrust force model is beneficial for the orbit determination of a maneuvered GEO satellite;the two-way adaptive Kalman filter can efficiently control the influence of the dynamic model errors on the orbit state estimate. | XU TianHe HE KaiFei XU GuoChang | 2012 | Science China(Physics,Mechanics & Astronomy)2012，55，4： | 2 |
| 17 | Satellite orbit determination by transfer with differenced ranges显示文摘The original idea of orbit determination called 'determination of satellite orbit by transfer' was proposed by the National Time Service Center,Chinese Academy of Sciences.It shows that the system is very stable and the orbit determination accuracy is improved greatly.A new observation mode called 'differenced ranges between master station and slave stations by transfer' is introduced.It is the development of 'determination of satellite orbit by transfer'.In principle,the differenced ranges between master station and slave stations have a high angular resolution,and strongly constrains in the transverse direction of satellite orbit,perpendicular to the line-of-sight.The principle of 'differenced ranges between master station and slave stations by transfer' is discussed in detail.And differenced ranges in combination with ranging data were used to determine satellite's orbit and orbit prediction under different arc observations.It shows that orbit determination accuracy for orbit prediction can be improved with differenced ranges in combination with ranging data. | YANG Ying LI ZhiGang YANG XuHai FENG ChuGang CAO Fen | 2012 | Chinese Science Bulletin2012，57，36： | 2 |
| 18 | Satellite orbit determination combining C-band ranging and differenced ranges by transfer显示文摘The constraint in the transverse direction of satellite orbit with differenced ranges between master station and slave stations by transfer as an angular observation data is explained in theory. Differenced ranges in combination with C-band ranging by transfer were used in satellite orbit determination. The position error of overlapped orbit differences for combining is less than that for ranging only. The residual of predicted orbit forward 5.5 days for combining is 3.1762 m, while the residual for ranging only with the same duration is 3.5380 m. Both the orbital overlapping and orbit prediction experimentations can testify the constraint in the transverse direction of satellite orbit with differenced ranges, and the results show that the accuracy of orbit determination and orbit prediction is improved by combining differenced ranges and C-band ranging. | YANG Ying YANG XuHai LI ZhiGang FENG ChuGang | 2013 | Chinese Science Bulletin2013，58，19： | 1 |
| 19 | FY-4A静止气象卫星转发器时延在轨标定显示文摘观测数据的系统差是影响卫星定轨精度的主要因素,其中卫星转发器时延由于难以直接在轨测量获取,因此成为FY-4A静止气象卫星观测数据系统差的主要来源之一。针对该问题,首先对原有的FY-4A静止气象卫星转发器时延在轨标定方案进行了介绍并分析,发现该方案由于待估参数过多导致无法获得卫星转发器时延,随后提出了一种新的在轨标定方法,利用动力学精密定轨分析得到FY-4A气象卫星转发器时延与地面校正值差异在2 m左右,结果表明该方法可以有效的反演FY-4A气象卫星转发器时延在轨变化情况。 | 鲁文强 黄勇 | 2021 | 电子测量技术2021，44，3： | 1 |
| 20 | 混合星座条件下的多星定轨及其精度显示文摘为了实现与确保区域导航服务能力,COMPASS设计采用GEO/tGSO/MEO混合星座,利用区域监测网完成卫星轨道测定与预报,并通过预报星历确保导航服务。在区域布站条件下,难以实现对IGSO/MEO卫星的全弧段跟踪;混合星座条件下,不同卫星的动力学特性存在一定的差异,尤其是首次采用GEO卫星,其静地特性致使轨道与钟差强相关,为动力学模型选取带来一定的困难。这些不利因素都给轨道确定带来一定的挑战。本文给出了区域监测网条件下多星定轨的测量模型与动力学模型,设计了轨道与钟差参数的解算方案,系统地分析与论证了区域布站条件下的混合星座定轨精度。试验表明,卫星三维位置精度优于2m,基于激光数据检验的GEO卫星轨道预报2h视向精度优于0.3m.IGSO卫星轨道预报6h视向精度优于0.4m。 | 胡光明 郭睿 李晓杰 吴杉 | 2015 | 测绘科学与工程2015，35，2： | 0 |
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