航天INSAR复影像对的自动快速匹配

针对航天INSAR主、辅影像数据的特点，提出了加大匹配窗口、加大锚点间隔的匹配策略，以提高匹配的可靠性和速度。在匹配过程中，综合利用轨道参数和强度影像金字塔进行粗匹配，并对强度影像采用相关系数与最小二乘相结合的双向匹配方案，实现了自动、快速、高可靠性和高精度的航天INSAR复影像匹配。最后总结了航天INSAR复影像匹配的特点。     

FY-3E: The First Operational Meteorological Satellite Mission in an Early Morning Orbit

Fengyun-3 E(FY-3E),the world’s first early-morning-orbit meteorological satellite for civil use,was launched successfully at the Jiuquan Satellite Launch Center on 5 July 2021.The FY-3E satellite will fill the vacancy of the global early-morning-orbit satellite observation,working together with the FY-3C and FY-3D satellites to achieve the data coverage of early morning,morning,and afternoon orbits.The combination of these three satellites will provide global data coverage for numerical weather prediction(NWP)at 6-hour intervals,effectively improving the accuracy and time efficiency of global NWP,which is of great significance to perfect the global earth observing system.In this article,the background and meteorological requirements for the early-morning-orbit satellite are reviewed,and the specifications of the FY-3E satellite,as well as the characteristics of the onboard instrumentation for earth observations,are also introduced.In addition,the ground segment and the retrieved geophysical products are also presented.It is believed that the NWP communities will significantly benefit from an optimal temporal distribution of observations provided by the early morning,mid-morning,and afternoon satellite missions.Further benefits are expected in numerous applications such as the monitoring of severe weather/climate events,the development of improved sampling designs of the diurnal cycle for accurate climate data records,more efficient monitoring of air quality by thermal infrared remote sensing,and the quasicontinuous monitoring of the sun for space weather and climate.     

晕轨道X射线脉冲星自主导航和轨道维持研究

目的 提出一种利用X射线脉冲星的晕轨道自主导航方法。以高精度星历轨道动力学模型构建晕轨道状态方程,并利用二级微分修正方法获取惯性系下晕轨道的标称轨道。基于微分修正原理,利用 X射线脉冲星的导航结果和小推力推进器,对晕轨道探测器进行轨道维持和控制,并以地月系 L2点晕轨道为例进行了仿真实验。结果表明,该方法能够有效完成地月系L2点晕轨道探测器的自主导航和轨道维持任务。     

改进的能量守恒方法及其在CHAMP重力场恢复中的应用

An efficient method for gravity field determination from CHAMP orbits and accelerometer data is referred to as the energy balance approach. A new CHAMP gravity field recovery strategy based on the improved energy balance approach IS developed in this paper. The method simultaneously solves the spherical harmonic coefficients, daily Integration constant, scale and bias parameters. Two 60 degree and order gravitational potential models, XISM-CHAMPO1S from the classical energy balance approach, and XISM-CHAMPO2S from the improved energy balance, are determined using about one year＇s worth of CHAMP kinematic orbits from TUM and accelerometer data from GFZ. Comparisons among XISM-CHAMPO1S, XISM-CHAMPO2S, EIGEN-CGO3C, EIGEN-CHAMPO3S, EIGEN2, ENIGNIS and EGM96 are made. The results show that the XISM-CHAMPO2S model is more accurate than EGM96, EIGENIS, EIGEN2 and XISM-CHAMPO1S at the same degree and order, and has almost the same accuracy as EIGEN-CHAMPO3S.     

基于GNSS和SLR观测数据的北斗卫星(GEO/IGSO)精密定轨

研究了联合GNSS和卫星激光测距（satellite laser ranging,SLR）观测数据对北斗卫星定轨精度的影响。仅利用GNSS观测值对北斗卫星进行定轨时,C01、C08和C10卫星的SLR检核结果显示,这3颗卫星的SLR残差均存在一定的偏差且不相同。加入SLR观测值联合定轨时,分别对估计和不估计系统偏差的卫星轨道结果进行分析。结果显示,对C01（GEO）卫星加入SLR观测值时必须引入系统偏差,否则会使轨道偏离;C08和C10（IGSO）卫星估计和不估计系统偏差时对预报轨道的精度均有一定的改善。最后统计了这3颗卫星的系统偏差,C01卫星的系统偏差达到50 cm,C08和C10卫星的系统偏差在5 cm以内。     

利用SLR数据检核GLONASS卫星最终轨道

采用由EDC提供的2015-01-01～2015-12-31的SLR标准点观测数据进行GLONASS卫星最终轨道（CODE提供）检核,分别按照卫星PRN号和不同测站对检核结果进行统计分析。结果表明,不同卫星的检核效果参差不齐,跟卫星的服役年限有关,较新的卫星检核结果较好,第一轨道面的卫星检核结果最好;检核结果中存在一定的系统误差,且大部分的激光测距比最终轨道反算的站星距要短;利用SLR检核2015年全年GLONASS轨道精度总体优于3.3 cm,激光观测精度总体优于1.2 cm。     

不同数据预处理方法对北斗卫星精密定轨精度的影响

提出综合利用高次差法和多项式拟合法对COMPASS MEO卫星进行周跳探测的原理及实现方法,并采用COMPASS监测站实测数据使用不同的数据预处理策略对COMPASS MEO卫星进行精密定轨试验。结果表明,根据实测数据情况,合理选择周跳探测方法和预处理策略,可以改善定轨精度。     

两种电离层延迟改正模型对星载单频GPS实时定轨精度的影响

采用单频星载GPS实测伪距和载波相位观测值,结合不同的电离层延迟改正模型进行模拟实时定轨实验,分析单频实时定轨的精度。不同轨道高度的低轨卫星实验结果表明,在卫星轨道较高(500 km以上)时,使用单频伪距观测值与改进的Klobuchar模型,实时定轨位置精度可达0.86 m(三维RMS),速度精度可达0.9 mm/s,接近甚至优于双频伪距实时定轨的轨道精度;使用单频码相无电离层组合观测值时,实时定轨位置精度可达0.54 m,速度精度可达0.55 mm/s。采用合适的电离层延迟改正模型,廉价的单频星载接收机可应用于微小卫星的实时定轨。     

北斗三号组网卫星数据质量分析及单系统定轨精度初步评估

选取2018-01-23起10 d内16个iGMAS测站观测数据,对北斗三号卫星的观测数据质量及BDS单系统精密定轨精度进行评估。初步结果表明,老信号B1I、B3I北斗三号卫星的信噪比略强于二号卫星,噪声与多路径基本相当,均在0.1 m量级,新卫星不存在星内多路径偏差。新信号B1C/L1/E1频点GPS信噪比最强,Galileo和BDS卫星相当,B2a/L5/E5a和B2b/E5b各系统基本相当;噪声及多路径方面,B1C/L1/E1频点GPS优于BDS、Galileo卫星0.1 m量级,B2a/L5/E5a和B2b/E5b各系统基本相当,均在0.1 m量级,新信号中北斗三号卫星星内多路径偏差基本消失。单系统精密定轨试验中,分别进行有/无GEO卫星策略、太阳光压模型ECOM 五/九参数策略的比较,并使用卫星激光测距数据进行独立检核。初步结果表明,有GEO卫星、ECOM五参数光压模型的定轨精度最好,C19号卫星7个重叠弧段的平均定轨精度在沿迹向、法向、径向的精度分别为32 cm、16 cm、8 cm,与试验卫星的定轨精度基本相当。     

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