共查询到15条相似文献，搜索用时 656 毫秒
1.
《武汉大学学报(信息科学版)》2020,(6)
2015年以来陆续发射入轨的北斗全球卫星导航系统(简称北斗三号系统,BeiDou global navigation satellite system,BDS-3)卫星,其姿态控制增加了连续动态偏置模式,为研究BDS-3卫星在地影期间的定轨精度提供了条件。首先利用ECOM (empirical CODE(Center for Orbit Determination in Europe) orbit model)系列模型评估了BDS-3卫星的光压摄动建模精度和定轨精度,同时以轨道重叠弧段精度、用户等效距离误差(user equivalent range error,UERE)、卫星激光测距(satellite laser ranging, SLR)残差和定位精度为指标,对基本导航模式下BDS-3卫星的定轨精度进行了评估。然后基于北斗60余天的实测数据进行了实验,结果表明,BDS-3卫星克服了区域系统卫星在姿态控制模式转换期间定轨精度下降的问题,其定轨精度与动态偏置期间定轨和预报精度相当,仅下降2～3 cm,定位精度下降1 cm,这与目前北斗的定轨精度和定位精度相比,可以忽略。进一步的分析表明,采用ECOM 5参数光压模型,连续动偏期间的轨道重叠弧段精度为0.26 m,预报2 h的UERE均方根降低至1.22 m,SLR残差的均方根小于0.31 m,大大提升了北斗系统的可用性。 相似文献
2.
当前的北斗卫星导航系统尚缺乏合适的太阳光压模型,由GPS的ECOM模型衍生而来的多种经验光压模型常被用于北斗定轨中。从观测值残差、轨道内、外符精度以及外推精度等方面比较分析了目前常用的4种经验光压模型对于北斗卫星定轨的适用性。结果表明,不同(类型)卫星适用不同的经验光压模型,但总体来看,9参数模型的适用性最差,而5参数和7参数模型的适用性相对较好。 相似文献
3.
太阳光压摄动作为在轨导航卫星受到的最大的非保守力,是卫星精密定轨的重要误差源。ECOM模型、ECOM2模型,这两种经验型光压模型被广泛应用于导航卫星定轨。然而,ECOM模型和ECOM2模型分别是针对GPS和GLONASS卫星设计的,并不完全适用于我国北斗三号(BDS-3)卫星。针对五参数ECOM模型在BDS-3卫星低太阳高度角时期轨道不连续性增大的问题,本文提出在 D方向引入一阶周期项来吸收未被模型化光压加速度。结果表明,引入一阶余弦周期项 Dc,能将低太阳高度角时期CAST卫星的切向、法向、径向重叠轨道误差分别减小约60%、52%、29%。针对ECOM2模型中 D2c和 D0、D2s和 Bs之间存在的强相关性,本文提出了不估计 D2c参数的八参数ECOM2模型和不估计 D2c与 D2s的七参数ECOM2模型。结果表明,相较九参数ECOM2模型,不估计 D2c参数的八参数ECOM2模型能够将CAST卫星和SECM卫星径向重叠轨道误差分别减少约18%和27%。在此基础上,继续移除 D2s后(七参数ECOM2),径向重叠轨道误差可进一步减小5.2%~8.5%。综合考察重叠轨道精度和SLR检核精度,不顾及 D2c和 D2s的七参数ECOM2模型表现最佳。CAST卫星和SECM卫星重叠轨道切向、法向、径向精度分别为5.0、3.4、1.4 cm和5.4、3.5、1.5 cm;SLR检核残差标准差分别为3.1~3.2 cm、4.4~4.7 cm。 相似文献
4.
卫星帆板及本体受照情况变化复杂,导致卫星光压摄动力的变化难以准确模制,既是动力学定轨的最大误差源,也是定轨预报精度降低的主要原因。针对此问题,采用北斗地面系统的区域监测网数据,详细比较了3种主要的经验模型（T20模型、ECOM5参数模型、ECOM9参数模型）对不同卫星的适用性情况。结果显示,在春秋分前后,地球同步轨道（geosynchronous earth orbit,GEO）卫星使用ECOM9参数模型最好,其解算的卫星钟差与星地双向钟差的互差标准差优于2 ns;对于倾斜地球同步轨道（inclined geosynchronous satellite orbit,IGSO）卫星和中地球轨道（medium earth orbit,MEO）卫星,无论是在动偏期间还是姿态模式转换期间,T20模型表现出更好的适用性。不同于此前国内外学者的相关研究,试验表明,对BDS混合星座的不同类型卫星、同一卫星的不同时段,应采用不同的经验太阳光压模型,以获得更高的定轨和预报精度。 相似文献
5.
以ECOM经验光压模型为基础,利用北斗卫星3年的精密星历进行轨道拟合,获得了ECOM光压参数的变化规律,给出了北斗3类卫星的ECOM光压参数选择策略。从北斗卫星姿态控制模式出发,通过卫星星体受照分析,指出在北斗卫星地影期零偏航状态下,由于太阳对卫星帆板的不正照,导致与动态偏航姿态相比,光压摄动力存在与轨道周期相关的分量,需要在ECOM 5参数的基础上增加D向周期分量进行吸收。通过MGEX全球网数据定轨试验,本文提出的方法可使零偏段定轨重叠段位置精度提高50%~80%。 相似文献
6.
太阳光压摄动是影响卫星定轨中重要的误差源,在GNSS导航卫星精密定轨过程中使用最为广泛的光压模型为ECOM模型。为了探究几种ECOM模型及其适用性,该文以超快速星历为起算轨道,分析对比经典ECOM-1模型与最新13参数ECOMC模型对GPS/BDS卫星轨道的影响。结果显示:相较于ECOM-1模型,ECOMC模型在GPS定轨中精度有所提升,特别体现在径向精度提升,单天与三天弧段在径向的解算精度分别提升了12.73%和24.74%;在BDS定轨中,采用ECOMC模型,部分GEO卫星在径向方向单天精度有12.38%的提升,而对于IGSO与MEO卫星二者精度差异不大;分析可得,由于星体结构不对称引起卫星在沿太阳-卫星方向作用的偶数阶短周期谐波扰动,引入卫星-太阳方向偶数阶项的参数估计可提升卫星径向精度。 相似文献
7.
针对北斗三号卫星导航系统(BDS-3)五频点观测数据和非差非组合精密定轨理论，介绍了非差非组合观测模型和参数估计方法，提出了利用K均值聚类算法(K-means)进行测站选取的策略，分析并讨论了非差非组合方法的优势.通过K-means和人工经验选取两种测站选取方案，分别使用BDS-3五频，B1C+B2a、B1I+B3I三种频率选择方式，利用30个观测站，对BDS-3中轨道地球卫星(MEO)和倾斜地球同步轨道卫星(IGSO)进行精密定轨处理.结果表明：当接收B1C+B2a频点观测数据测站不足时，非差非组合方法可以通过利用五频观测数据增加观测数据数量、优化测站布局，提高定轨精度，与B1C+B2a频率组合相比，五频定轨结果切向(A)、法向(C)、径向(R)和三维(3D)方向均方根(RMS)月均值分别提升0.003 m、0.004 m、0.003 m和0.007m;K-means算法选取的测站与人工经验选取相比，分布更加合理，定轨精度更高，三种频率选择方案MEO卫星3D RMS月均值精度分别提升0.009 m、0.017 m和0.009 m. 相似文献
8.
光压模型是导航卫星高精度定轨、定位的基础。目前关于北斗卫星光压摄动模型的研究并不少见,但基于卫星物理参数的综合解析模型建立与应用公开可见的论述并不多见。不同于其他保守和非保守摄动力,光压辐射与卫星本身参数状态密切相关,具有明显的个体差异性。本文基于光压辐射的物理机理、北斗卫星物理参数、姿态控制模式等,建立光压摄动综合解析模型,以精密星历和激光测距数据为基准,验证了综合解析模型能够获得分米级的精密定轨精度。在此基础上,根据卫星角动量守恒和在轨遥测参数变化,分析了综合解析模型和在轨实际干扰力的差值,提出了在综合解析模型基础上增加常数经验修正项Da、Ya的方法,以北斗C08、C10星为例,分别可获得0.078、0.084 m的SLR检核精度,相比于利用CODE经验改进模型,精度分别提高0.021、0.045 m。 相似文献
9.
为了研究轨道预报期间光压模型的影响,该文采用2017年8月1日至2017年11月30日的事后精密轨道产品,研究ECOM 5参数模型、ECOM 9参数模型和可校正Box-wing模型对BDS-IGSO/MEO卫星和Galileo卫星轨道预报的影响。预报轨道通过与事后精密轨道对比以及激光检核得到的残差来评价其精度。对于BDS-IGSO/MEO卫星,ECOM 5参数模型和ECOM 9参数模型结果基本一致,可校正Box-wing模型最差,但是在卫星径向精度上,ECOM 9参数模型要优于ECOM 5参数模型。对于Galileo卫星,ECOM 9参数模型要整体优于ECOM 5参数模型。 相似文献
10.
《武汉大学学报(信息科学版)》2021,(3)
针对BDS-2与BDS-3卫星之间的差异性,为实现观测数据深度融合,对BDS-2/BDS-3联合定轨中系统偏差(inter-satellite bias,ISB)模型进行研究。首先,基于奇异值分解提取相邻历元观测信息以增加数据利用率,提高ISB解算精度与可靠性;其次,分析了BDS-2/BDS-3联合定轨中ISB特性,发现新信号与BDS-2之间存在明显与接收机相关偏差;随后,利用定轨法方程求解ISB与轨道相关性,结果显示,ISB对北斗轨道精度影响较GPS(global positioning system)显著;最后,通过对ISB时间序列建立短期预报模型,并将预报值作为约束条件引入超快速定轨中。实验结果表明,针对BDS-2/BDS-3超快速轨道,利用提出的ISB的估计与预报模型,可分别改善BDS-2与BDS-3轨道18 h重叠弧段精度(一维)-0.4～1.0 cm与0.8～4.1 cm。因此,所提出的改进的ISB处理模型对优化BDS-2/BDS-3联合定轨策略具有一定参考意义。 相似文献
11.
It has been noted that the satellite laser ranging (SLR) residuals of the Quasi-Zenith Satellite System (QZSS) Michibiki satellite orbits show very marked dependence on the elevation angle of the Sun above the orbital plane (i.e., the \(\beta \) angle). It is well recognized that the systematic error is caused by mismodeling of the solar radiation pressure (SRP). Although the error can be reduced by the updated ECOM SRP model, the orbit error is still very large when the satellite switches to orbit-normal (ON) orientation. In this study, an a priori SRP model was established for the QZSS Michibiki satellite to enhance the ECOM model. This model is expressed in ECOM’s D, Y, and B axes (DYB) using seven parameters for the yaw-steering (YS) mode, and additional three parameters are used to compensate the remaining modeling deficiencies, particularly the perturbations in the Y axis, based on a redefined DYB for the ON mode. With the proposed a priori model, QZSS Michibiki’s precise orbits over 21 months were determined. SLR validation indicated that the systematic \(\beta \)-angle-dependent error was reduced when the satellite was in the YS mode, and better than an 8-cm root mean square (RMS) was achieved. More importantly, the orbit quality was also improved significantly when the satellite was in the ON mode. Relative to ECOM and adjustable box-wing model, the proposed SRP model showed the best performance in the ON mode, and the RMS of the SLR residuals was better than 15 cm, which was a two times improvement over the ECOM without a priori model used, but was still two times worse than the YS mode. 相似文献
12.
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。 相似文献
13.
北斗卫星天线相位中心改正模型精化及对精密定轨和定位影响分析 总被引：1，自引：0，他引：1
针对BDS-2和BDS-3卫星联合精密定轨和精密定位中高精度BDS-2 IGSO/MEO卫星天线相位中心改正在轨估计模型的缺失问题,本文采用了改进的PCV和z-offset参数估计方法,精化了BDS-2 IGSO/MEO卫星B1I/B3I无电离层组合PCC模型。数值验证结果表明：相比北斗官方发布的PCO地面标定值,本文精化的PCC模型使得精密轨道SLR残差的STD减小了0.6~2.4 cm,改善百分比为8.6%~33.3%;基于本文精化的BDS-2和已有BDS-3卫星精化的PCC模型使得精密定位浮点解在高程方向显著提升了9.5 mm（37.2%）。 相似文献
14.
CODE’s five-system orbit and clock solution—the challenges of multi-GNSS data analysis 总被引：1，自引：1，他引：0
Lars Prange Etienne Orliac Rolf Dach Daniel Arnold Gerhard Beutler Stefan Schaer Adrian Jäggi 《Journal of Geodesy》2017,91(4):345-360
This article describes the processing strategy and the validation results of CODE’s MGEX (COM) orbit and satellite clock solution, including the satellite systems GPS, GLONASS, Galileo, BeiDou, and QZSS. The validation with orbit misclosures and SLR residuals shows that the orbits of the new systems Galileo, BeiDou, and QZSS are affected by modelling deficiencies with impact on the orbit scale (e.g., antenna calibration, Earth albedo, and transmitter antenna thrust). Another weakness is the attitude and solar radiation pressure (SRP) modelling of satellites moving in the orbit normal mode—which is not yet correctly considered in the COM solution. Due to these issues, we consider the current state COM solution as preliminary. We, however, use the long-time series of COM products for identifying the challenges and for the assessment of model-improvements. The latter is demonstrated on the example of the solar radiation pressure (SRP) model, which has been replaced by a more generalized model. The SLR validation shows that the new SRP model significantly improves the orbit determination of Galileo and QZSS satellites at times when the satellite’s attitude is maintained by yaw-steering. The impact of this orbit improvement is also visible in the estimated satellite clocks—demonstrating the potential use of the new generation satellite clocks for orbit validation. Finally, we point out further challenges and open issues affecting multi-GNSS data processing that deserves dedicated studies. 相似文献
15.
S. Hackel O. Montenbruck P. Steigenberger U. Balss C. Gisinger M. Eineder 《Journal of Geodesy》2017,91(5):547-562
The radar imaging satellite mission TerraSAR-X requires precisely determined satellite orbits for validating geodetic remote sensing techniques. Since the achieved quality of the operationally derived, reduced-dynamic (RD) orbit solutions limits the capabilities of the synthetic aperture radar (SAR) validation, an effort is made to improve the estimated orbit solutions. This paper discusses the benefits of refined dynamical models on orbit accuracy as well as estimated empirical accelerations and compares different dynamic models in a RD orbit determination. Modeling aspects discussed in the paper include the use of a macro-model for drag and radiation pressure computation, the use of high-quality atmospheric density and wind models as well as the benefit of high-fidelity gravity and ocean tide models. The Sun-synchronous dusk–dawn orbit geometry of TerraSAR-X results in a particular high correlation of solar radiation pressure modeling and estimated normal-direction positions. Furthermore, this mission offers a unique suite of independent sensors for orbit validation. Several parameters serve as quality indicators for the estimated satellite orbit solutions. These include the magnitude of the estimated empirical accelerations, satellite laser ranging (SLR) residuals, and SLR-based orbit corrections. Moreover, the radargrammetric distance measurements of the SAR instrument are selected for assessing the quality of the orbit solutions and compared to the SLR analysis. The use of high-fidelity satellite dynamics models in the RD approach is shown to clearly improve the orbit quality compared to simplified models and loosely constrained empirical accelerations. The estimated empirical accelerations are substantially reduced by 30% in tangential direction when working with the refined dynamical models. Likewise the SLR residuals are reduced from \(-3\,\pm \,17\) to \(2\,\pm \,13\) mm, and the SLR-derived normal-direction position corrections are reduced from 15 to 6 mm, obtained from the 2012–2014 period. The radar range bias is reduced from \(-10.3\) to \(-6.1\) mm with the updated orbit solutions, which coincides with the reduced standard deviation of the SLR residuals. The improvements are mainly driven by the satellite macro-model for the purpose of solar radiation pressure modeling, improved atmospheric density models, and the use of state-of-the-art gravity field models. 相似文献