GPS卫星精密定轨中的摄动力分析

在介绍各种摄动模型的基础上,将IGS提供的SP3精密星历作为几何轨道,应用不同的摄动模型进行几何轨道平滑,求得卫星轨道的动力学参数,再用动力学参数积分求定卫星的轨道,将其与IGS提供的SP3精密星历进行比较,从而详细分析每一种摄动力对GPS轨道影响的量级,而且说明建立的GPS卫星轨道的摄动模型是比较准确的。     

IAU2000决议对卫星轨道的影响

研究了IAU2000对GPS卫星轨道确定的影响。以2006年DOY186的GPS数据为例,分析了GPS卫星在IAU2000决议模型以及原有模型下,惯性参考系统以及地固坐标系中轨道的差别。结果显示,采用不同模型,卫星轨道在惯性参考系中的差值存在周期性,其中X、Z方向的幅度达到了2.5 m,Y方向的幅度约为1 m;在地固系中,轨道差别也存在周期,幅度约为4 mm。并对卫星轨道的差值进行了统计,得出了在惯性系下,不同模型引起轨道差值的3D RMS为m级。     

Reducing Influence of Gravity Model Error in Precise Orbit Determination of Low Earth Orbit Satellites

Based on the orbit integration and orbit fitting method, the influence of the characters of the gravity model, with different precisions, on the movement of low Earth orbit satellites was studied. The way and the effect of absorbing the influence of gravity model error on CHAMP and GRACE satellite orbits, using linear and periodical empirical acceleration models and the so-called "pseudo-stochastic pulses" model, were also analyzed.     

近圆轨道卫星交叉点概略位置理论计算

轨道交叉点在标校卫星系统偏差参数、评估卫星载荷性能以及卫星精密定轨方面具有重要作用.针对现有轨道交叉点计算多采用搜索法结合多项式拟合方法,虽能够获取精确交叉点位置但较难分析交叉点整体分布特征的问题,该文从二体问题解析解出发,推导了交叉点概略位置理论计算公式,并分析了不同卫星轨道交叉点特性,提出了基于交叉点函数的计算方法,并用仿真试验数据对本文方法有效性进行了验证.该文方法为分析交叉点概略位置空间分布特性提供了一种思路.     

绕月飞行器近圆形轨道演化的数值分析

利用GSFC/NASA/USA的GEODYNⅡ软件,并引入JPL/NASA/USA最新的165×165阶次的月球重力场模型LP165P,通过对该模型进行截断,仿真计算了不同阶次的月球重力场模型对轨道演化的影响,在相同的重力场模型下,计算了不同轨道高度、不同倾角和不同轨道偏心率的轨道演化情况。大量的仿真计算表明,高倾角、圆轨道的中低轨(150 km或200 km)绕月飞行器具有相对稳定的轨道演化特征,在不进行任何调整的情况下,其轨道持续运行时间超过1 a。同时计算表明,轨道积分过程中可以截断月球重力场模型至100阶次而不损失精度。     

地月系Halo轨道族的分岔研究

讨论了利用单值矩阵的特征值研究Halo周期轨道稳定性和分岔特性的方法;建立了稳定阶数用于对周期轨道稳定性进行定性评判;系统地研究了对周期轨道拟周期分岔、正切分岔和n倍周期分岔.最后计算了地月系L1点附近Halo轨道族的稳定性和分岔,指出分岔轨道将在深空探测轨道设计中发挥独特的作用.     

一种改进的高铁无砟轨道检测方法

无砟轨道的静态检测通常是沿着轨道线路对轨枕逐个检测,这样做虽然能够满足工程精度的需要但是工作效率较低。文中通过比较不同的插值方法的优缺点,最终选择通过三次样条插值对静态轨道检测的隔轨数据进行处理,并结合贵广高铁检测工程在采用不同的测量方案下,对高铁线路直线段和曲线段的插值结果进行分析。并且用内插后的轨检数据结果与连续测量后得到的轨检数据进行比较,得出不同条件下最有效、最准确的测量与数据处理的实施方案,工程实践证明,文中提出的检测与数据处理手段具有准确性和高效性。     

航天器轨道向导式设计器的设计与实现

航天器轨道设计因卫星应用目的和总体设计方案的不同而灵活多样.文中在对航天器轨道设计方法归纳总结的基础上,采用组件方式设计了向导式轨道设计器.该设计器能够实现太阳同步轨道等典型轨道的初始轨道设计任务,通过与卫星工具软件(STK)设计结果的比较,验证了设计器的正确性.     

地月系Halo轨道族的分岔研究

讨论了利用单值矩阵的特征值研究Halo周期轨道稳定性和分岔特性的方法;建立了稳定阶数用于对周期轨道稳定性进行定性评判;系统地研究了对周期轨道拟周期分岔、正切分岔和n倍周期分岔。最后计算了地月系L1点附近Halo轨道族的稳定性和分岔,指出分岔轨道将在深空探测轨道设计中发挥独特的作用。     

航天器轨道向导式设计器的设计与实现

航天器轨道设计因卫星应用目的和总体设计方案的不同而灵活多样。文中在对航天器轨道设计方法归纳总结的基础上,采用组件方式设计了向导式轨道设计器。该设计器能够实现太阳同步轨道等典型轨道的初始轨道设计任务,通过与卫星工具软件(STK)设计结果的比较,验证了设计器的正确性。     

IGR轨道外推及其在对流层实时监测中的应用研究

在精密定轨和轨道外推理论的基础上，对比分析了由IGS快速轨道（IGS rapid orbit，IGR）外推1d的轨道与IGS最终轨道间的差异，用此外推轨道和最终轨道分别按长基线双差网解方案计算了BRUS、IENG、PTBB等欧洲一些IGS／TAI站的天顶湿延迟（zenith wet delay，ZWD），并对两种轨道下各站的ZWD进行了对比。轨道对比结果显示，除异常卫星外，“病态”卫星的IGR外推1d的轨道仍具有一定的高精度。而ZWD的对比结果则表明，当剔除异常卫星的影响并对“病态”卫星加以适当处理后，IGR外推1d的轨道用于对流层实时监测是可行的。     

Long-arc analyses of SLR observations of the Etalon geodetic satellites

In this paper we describe the results of an analysis of a 2.5-year set of satellite laser range observations of the two Etalon geodetic satellites. We fit continuous orbits to the range observations, and map the range residuals into series of equivalent orbital element residuals, considering in detail the orbital longitude, eccentricity and nodal residuals. We use the longitude residuals to study thermal effects acting on the satellites and compare the results with those published for the Lageos satellites. We discuss the differences between the two series of eccentricity residuals, and again compare the results with those from Lageos. Finally we use the nodal residuals to investigate the potential for determination of UT1 of the reference frame defined by the orbits of the Etalon satellites. Received: 30 January 1997 / Accepted: 11 December 1997     

SLR资料精密测定GLONASS卫星轨道

将SLR资料计算的轨道与CODE轨道进行了比较，并将比较结果转换到RTN坐标系中。通过比较分析发现，两种轨道差值在轨道径向、法向和沿轨方向的精度分别优于10cm、50cm和45cm；SLR和微波资料确定的GLONASS卫星轨道在径向存在系统误差，该系统误差随卫星轨道面的不同而不同。     

Validation of Galileo orbits using SLR with a focus on satellites launched into incorrect orbital planes

The space segment of the European Global Navigation Satellite System (GNSS) Galileo consists of In-Orbit Validation (IOV) and Full Operational Capability (FOC) spacecraft. The first pair of FOC satellites was launched into an incorrect, highly eccentric orbital plane with a lower than nominal inclination angle. All Galileo satellites are equipped with satellite laser ranging (SLR) retroreflectors which allow, for example, for the assessment of the orbit quality or for the SLR–GNSS co-location in space. The number of SLR observations to Galileo satellites has been continuously increasing thanks to a series of intensive campaigns devoted to SLR tracking of GNSS satellites initiated by the International Laser Ranging Service. This paper assesses systematic effects and quality of Galileo orbits using SLR data with a main focus on Galileo satellites launched into incorrect orbits. We compare the SLR observations with respect to microwave-based Galileo orbits generated by the Center for Orbit Determination in Europe (CODE) in the framework of the International GNSS Service Multi-GNSS Experiment for the period 2014.0–2016.5. We analyze the SLR signature effect, which is characterized by the dependency of SLR residuals with respect to various incidence angles of laser beams for stations equipped with single-photon and multi-photon detectors. Surprisingly, the CODE orbit quality of satellites in the incorrect orbital planes is not worse than that of nominal FOC and IOV orbits. The RMS of SLR residuals is even lower by 5.0 and 1.5 mm for satellites in the incorrect orbital planes than for FOC and IOV satellites, respectively. The mean SLR offsets equal \(-44.9, -35.0\), and \(-22.4\) mm for IOV, FOC, and satellites in the incorrect orbital plane. Finally, we found that the empirical orbit models, which were originally designed for precise orbit determination of GNSS satellites in circular orbits, provide fully appropriate results also for highly eccentric orbits with variable linear and angular velocities.     

Initial results of centralized autonomous orbit determination of the new-generation BDS satellites with inter-satellite link measurements

Autonomous orbit determination is the ability of navigation satellites to estimate the orbit parameters on-board using inter-satellite link (ISL) measurements. This study mainly focuses on data processing of the ISL measurements as a new measurement type and its application on the centralized autonomous orbit determination of the new-generation Beidou navigation satellite system satellites for the first time. The ISL measurements are dual one-way measurements that follow a time division multiple access (TDMA) structure. The ranging error of the ISL measurements is less than 0.25 ns. This paper proposes a derivation approach to the satellite clock offsets and the geometric distances from TDMA dual one-way measurements without a loss of accuracy. The derived clock offsets are used for time synchronization, and the derived geometry distances are used for autonomous orbit determination. The clock offsets from the ISL measurements are consistent with the L-band two-way satellite, and time–frequency transfer clock measurements and the detrended residuals vary within 0.5 ns. The centralized autonomous orbit determination is conducted in a batch mode on a ground-capable server for the feasibility study. Constant hardware delays are present in the geometric distances and become the largest source of error in the autonomous orbit determination. Therefore, the hardware delays are estimated simultaneously with the satellite orbits. To avoid uncertainties in the constellation orientation, a ground anchor station that “observes” the satellites with on-board ISL payloads is introduced into the orbit determination. The root-mean-square values of orbit determination residuals are within 10.0 cm, and the standard deviation of the estimated ISL hardware delays is within 0.2 ns. The accuracy of the autonomous orbits is evaluated by analysis of overlap comparison and the satellite laser ranging (SLR) residuals and is compared with the accuracy of the L-band orbits. The results indicate that the radial overlap differences between the autonomous orbits are less than 15.0 cm for the inclined geosynchronous orbit (IGSO) satellites and less than 10.0 cm for the MEO satellites. The SLR residuals are approximately 15.0 cm for the IGSO satellites and approximately 10.0 cm for the MEO satellites, representing an improvement over the L-band orbits.     

导航卫星受地球外辐射带影响仿真分析

目前国际上不同国家已经进行了多个导航系统的开发,而构成这些系统的关键空间段实体导航卫星通常分布在中高轨道上,通过地球辐射带对该空间区域内卫星的辐射影响进行仿真分析,对于中轨道空间辐射,当卫星屏蔽厚度大于9mm,再增加屏蔽厚度的方法对辐射隔离不再敏感;对于高轨道空间辐射,当卫星屏蔽厚度大于7mm,再增加屏蔽厚度方法对隔离辐射已经不再敏感。可见,仅从辐射加固角度来说,在卫星设计时,以10年寿命为例,对于中轨道卫星屏蔽厚度区间取[8,9]mm为宜,对于高轨道卫星屏蔽厚度区间取[6,7]mm为宜。     

利用GPS卫星轨道确定地球二阶带谐系数的研究

重力恢复和气候实验(gravity recovery and climate experiment,GRACE)任务受限于卫星的低轨极地轨道性质和编队模式,确定的重力场模型C20项存在不足.与之相比,全球定位系统(global positioning system,GPS)卫星为倾斜轨道,卫星数量多,将G PS卫星的精...     

Precise relative orbit determination of twin GRACE satellites

When formation flying spacecrafts are used as platform to gain earth oriented observation, precise baselines between these spacecrafts are always essential. Gravity recovery and climate experiment (GRACE) mission is aimed at mapping the global gravity field and its variation. Accurate baseline of GRACE satellites is necessary for the gravity field modeling. The determination of kinematic and reduced dynamic relative orbits of twin satellites has been studied in this paper, and an accuracy of 2 mm for dynamic relative orbits and 5 mm for kinematic ones can be obtained, whereby most of the double difference onboard GPS ambiguities are resolved.     

Galileo status: orbits,clocks, and positioning

The European Global Navigation Satellite System Galileo is close to declaration of initial services. The current constellation comprises a total of 12 active satellites, four of them belonging to the first generation of In-Orbit Validation satellites, while the other eight are Full Operational Capability (FOC) satellites. Although the first pair of FOC satellites suffered from a launch anomaly resulting in an elliptical orbit, these satellites can be used for scientific applications without relevant limitations. The quality of broadcast orbits and clocks has significantly improved since the beginning of routine transmissions and has reached a signal-in-space range error of 30 cm. Precise orbit products generated by the scientific community achieve an accuracy of about 5 cm if appropriate models for the solar radiation pressure are applied. The latter is also important for an assessment of the clock stability as orbit errors are mapped to the apparent clock. Dual-frequency single point positioning with broadcast orbits and clocks of nine Galileo satellites that have so far been declared healthy already enables an accuracy at a few meters. Galileo-only precise point positioning approaches a precision of 2 cm in static mode using daily solutions.     

基于平方根推广卡尔曼滤波的星载GPS定轨

本文探讨了利用星载GPS数据实现平方根推广卡尔曼滤波(SR-EKF)定轨的方法,采用SR-EKF对两颗GRACE卫星进行了定轨试验计算,并将计算结果与Bernese5.0的计算结果进行了比较,比较分析表明:采用SR-EKF方法进行GRACE卫星定轨可以得到优于10cm的定轨精度;经验力参数可以平衡几何观测信息和动力模型信息,但增大了观测异常对定轨结果的影响;对位置和速度进行噪声补偿可以减弱观测异常对定轨结果的影响,但有可能使轨道出现系统性偏差。