共查询到16条相似文献，搜索用时 187 毫秒
1.
越来越多的LEO卫星装载了高精度的星载GPS接收机,星载GPS定轨已成为LEO卫星精密定轨的重要手段之一。星载GPS精密定轨精度依赖于GPS星历及钟差精度,采用CODE(Center for Orbit Determination in Europe)官方网站提供的GPS精密星历及钟差数据,基于瑞士伯尼尔大学开发的Bernese 5.0软件,采用非差减缩动力学定轨方法,解算了60天的CHAMP卫星和SAC-C卫星轨道,并将所得轨道与JPL和GFZ事后科学轨道比较,得出的轨道位置三维精度优于20 cm量级,速度三维精度约为0.20 mm/s。 相似文献
2.
中高轨卫星广播星历精度分析 总被引：17，自引：0，他引：17
GPS广播星历参数具有物理意义明确、参数少、精度高等优点,可以考虑将它应用于其他卫星导航系统。但是GPS系统的卫星构成比较单一,而其他卫星导航系统可能包含中地球轨道 (MEO)、倾斜地球同步轨道(IGSO)和地球静止轨道(GEO)等多种不同类型的中高轨卫星。分析了采用GPS广播星历参数时,MEO、IGSO和GEO卫星的广播星历拟合精度,特别讨论了轨道倾角接近于0的GEO卫星的广播星历拟合精度,并给出了相应的改进措施。计算表明,对于 MEO卫星,2 h的广播星历拟合精度(三维位置)可达厘米级;对于IGSO卫星和轨道倾角较大的GEO卫星,4 h的广播星历拟合精度约为0．1 m,径向位置误差在厘米量级;而对于轨道倾角接近于0的GEO卫星,若不采取特殊措施,由于轨道倾角和升交点经度统计相关,其广播星历拟合精度很差,为此提出了一种坐标转换方法。采用此方法后的广播星历拟合精度可达0．1 m,径向位置误差为厘米量级。 相似文献
3.
目前,越来越多的低轨卫星上都搭载了用于精密定轨的星载GPs接收机,星载GPS已成为低轨卫星精密定轨的主要手段之一.星载GPS精密定轨精度依赖于GPS星历及钟差精度.基于SHORDE-Ⅲ非差动力学定轨功能,以2005年8月1日至8月7日一周的GRACE卫星实测数据为例,采用事后精密轨道(igs)、快速轨道(igr)和超快速轨道(igu)三种GPS星历在同等条件下定轨,估计GPS星历精度对低轨卫星定轨精度的影响,实际计算结果表明igs和igr两类GPS星历定轨精度相当,约为9.5 cm,igu星历定轨精度略低于igs和igr星历,约为10.5cm:高频GPS卫星钟差数据对定轨精度会产生1-6cm影响. 相似文献
4.
星载GPS相位观测值非差运动学定轨探讨 总被引：2，自引：0，他引：2
在几何法、动力学法和减缩动力学法定轨基础上，探讨了星载GPS相位观测值非差运动学定轨方法及其实现程序。该方法无需复杂的力学模型和地面资料，只需LEO(Low Earth Orbit)卫星上的GPS数据和IGS的GPS精密星历产品，它计算简单、方便，能快速、高精度地确定轨道，同时，还能确定一些动力学参数，但没有轨道预报功能；针对法方程系数矩阵比较庞大，提出了矩阵分块、上三角化的参数解算方法，并用CHAMP卫星资料分析了上述方法的定轨精度。 相似文献
5.
GPS定轨中的太阳辐射压模型 总被引：5，自引：0，他引：5
对于GPS这样的高轨卫星轨道的确定,最大的误差源为太阳辐射压摄动．近年来IGS各个数据处理中心提供的GPS星历精度越来越高,其中很重要的一个因素就是太阳辐射压摄动模型的不断完善．详细阐述了目前主要的7种太阳辐射压摄动模型后,给出了各种光压摄动模型的计算模型,并利用不同的摄动模型积分卫星轨道,得到不同模型在GPS卫星轨道积分中的精度．结果表明,Bern大学提供的3种模型对太阳辐射压的模拟较为准确,相对于其他4种模型,由其得到的GPS轨道精度有将近一个量级的提高． 相似文献
6.
北斗卫星导航系统SISURE初步评估 总被引：2，自引：0，他引：2
北斗导航系统自2018年12月27日提供全球服务以来,其服务性能受到了极大关注.以上海天文台iGMAS (International GNSS MonitoringAssessment System)分析中心发布的精密轨道、钟差产品作为基准,评估了2019年年积日3–12 d的北斗二号、北斗三号以及GPS广播星历的轨道、钟差和空间信号用户测距误差(Signal in Space User Ranging Error, SISURE,简称为URE),并且对北斗卫星导航系统结果进行了详细的分析.结果表明:在评估时间段内,北斗三号广播星历轨道精度、URE均明显优于北斗二号,且部分结果优于GPS.北斗三号广播星历轨道径向精度最高,优于0.2 m.北斗三号全部卫星URE均值优于0.4 m, URE RMS (root mean square)优于0.5 m.北斗二号每颗卫星URE均值、95%URE (置信度为95%的URE)、URE RMS小于2 m,北斗三号每颗卫星URE均值、95%URE、URE RMS小于1 m,均达到了系统公开承诺的服务性能标准. 相似文献
7.
8.
GPS星间链路及其数据的模拟方法研究 总被引：2，自引：0，他引：2
主要介绍了GPS星间链路（星间链路是卫星导航系统实现自主运行的一项重要的关键技术）的工作模式,重点讨论了GPS星间链路数据的模拟方法。采用契比雪夫多项式拟合方法,获得对IGS（International GPS Service）公布的GPS精密星历加密到以1 s为间隔的数据。由信号接收时刻获得的两颗卫星间的距离作为初始值,反复迭代推算出发射信号的卫星发射信号的时刻,从而得到两颗卫星间的星间伪距观测值,再加上各项约束条件（如噪声,钟差等）后获得了两颗卫星间模拟的星间链路数据。 相似文献
9.
对于在轨运行的BDS (BeiDou Navigation Satellite System)卫星, 太阳光压是作用在卫星上主要的非引力摄动. 受多种因素的影响, 太阳光压摄动力难以精确建模, 是BDS卫星精密定轨和轨道预报过程中重要的误差来源. 由于ECOMC (Empirical CODE Orbit Model 1 and 2 Combined)模型兼顾了ECOM1 (Empirical CODE Orbit Model 1)和ECOM2 (Empirical CODE Orbit Model 2)模型的特点, 在模型中引入了较多的待估参数, 使得参数之间存在强相关性. 针对ECOMC模型的这一缺陷, 文中收集了2019年1月至2022年4月武汉大学分析中心提供的BDS-3卫星精密星历, 采用动力学轨道拟合方法得到了ECOMC模型的13个光压参数. 通过对该模型的光压参数进行时间序列分析, 分别给出了BDS-3 IGSO (Inclined Geosynchronous Orbit)和MEO (Medium Earth Orbit)卫星光压模型的参数选择策略. 并利用轨道拟合和轨道预报试验, 验证了光压模型参数选择策略的合理性. 结果表明, 采用改进型ECOMC模型进行BDS-3 IGSO和MEO卫星轨道拟合的效果最佳, 同时, 也能够提升BDS-3 IGSO和MEO卫星中长期轨道预报的精度. 相似文献
10.
利用全球卫星激光测距服务系统(ILRS,International Laser Ranging Service)标准点资料对Ajisai卫星进行精密定轨,残差均方根(RMS)优于3 cm,得到该星的精密轨道.进而对长春站40 cm空间碎片光电望远镜获得的Ajisai卫星的天文定位资料进行精度分析,外符合精度约3″左右.单独利用天文定位数据进行轨道改进,内符合精度优于3″.改进轨道的x、y、z坐标3分量在观测数据覆盖范围内的精度在100 m之内.同样地对Jason-1卫星作数据分析,结果和Ajisai卫星精度相当.分析各个弧段的精度变化,发现定标星个数减少,会导致天文定位精度下降.据此提出可以把最少定标星比例作为评定数据质量的参考指标之一. 相似文献
11.
The satellite-borne GPS receivers dedicated to precise orbit determination are now being carried by more and more low earth orbit (LEO) satellites and the satellite-borne GPS has become one of the main means for the precise orbit determination of low earth orbit satellites. The accuracy of satellite-borne GPS precise orbit determination depends on the accuracies of the GPS ephemeris and the clock error. Based on the orbit determination function of SHORDEIII zero-difference dynamics and using the observational data obtained by the GRACE satellites for the week from 2005 August 1 to 7 as an example, three versions of GPS ephemerides (igs, igr and igu) are used to carry out orbit determination under the same conditions and to estimate the effect of the GPS ephemeris accuracy on the accuracy of orbit determination of low earth orbit satellites. Our calculated results show that the two ephemerides, igs and igr, are equivalent to each other in orbit determination accuracy (about 9.5 cm), while igu is slightly less accurate, at about 10.5 cm. The effect produced by the data of the high frequency GPS satellite clock error on the accuracy of orbit determination is 1–6 cm. 相似文献
12.
《Chinese Astronomy and Astrophysics》2005,29(2):213-222
When the GPS CV (common view) technique is used for the high-precision time comparisons, the effects of the error of the satellite orbit and the ionospheric delay of the received signal are not negligible and have to be IGS precise ephemeris and CODE global total electron content maps in the GPS time transfers, and it is shown that by using these IGS products the accuracies of the single-station time determination and long-distance time transfer can be effectively improved. 相似文献
13.
按照目前的国际规范, 高精度GNSS (Global Navigation Satellite System)轨道产品一般以天为周期进行发布, 提供给用户使用. 连续使用多天的产品存在不同天间的跳变问题. 利用德国地学研究中心(GFZ)、欧洲定轨中心(COD)、欧空局(ESA)、美国喷气试验室(JPL)以及上海天文台(SHA)共5个GNSS分析中心2013---2017年的轨道产品, 分析了轨道跳变的特性. 计算结果表明: GFZ、COD、ESA、SHA和JPL的3维轨道跳变平均分别为7.79cm、1.51cm、7.77cm、11.75cm和2.51cm. 轨道跳变序列的周期特性分析表明: 序列存在90d、120d、340d左右的显著周期项, 对应于海潮对地球自转的影响, 其振幅为数毫米至1cm左右. 表明精密轨道确定需要进一步精化该项模型; GPS的跳变序列还存在与卫星星座相关的175d和352d左右的交点年显著周期项. 此外, 针对COD产品外推轨道的分析, 验证了地球反照辐射压和太阳光压模型等动力学模型对轨道的差异. 相似文献
14.
Peter Kammeyer 《Celestial Mechanics and Dynamical Astronomy》2000,77(4):241-272
This paper discusses a UT1-like quantity, UTGPS, determined daily from Earth-referenced GPS satellite orbits from the International GPS Service (IGS). For each satellite considered, the observed relation between the satellite's IGS orbit and a model of its orbit plane in inertial space is used to estimate UT1. This modeled orbit plane is initialized using the satellite's IGS orbit and the actual UT1 at an initial time. It is then propagated using standard models of gravitational forces and an empirical model representing the orbit-normal radiation pressure observed during several years of in-flight experience with the satellite. To estimate UT1, an a-priori transformation from terrestrial to true-of-date celestial coordinates is applied to the satellite's IGS orbit. The geocentric angular deviations of points of the resulting transformed orbit from the modeled orbit plane are analyzed, giving the angle between the ascending nodes of the satellite's transformed and modeled orbit planes. To this observed angle between nodes, converted to a UT1 difference, is added the a-priori UT1 value used in the transformation. From the result is subtracted a model of the angle, again converted to a UT1 difference, between the ascending nodes of the actual and modeled orbit planes. The final result is the estimate of UT1 from this satellite, and the median of the UT1 estimates from all satellites considered is UTGPS. The root-mean-square difference between UTGPS-UT1 at the beginning and at the end of an interval of one to four weeks is approximately 30 s times the square root of the interval's duration in weeks.This revised version was published online in October 2005 with corrections to the Cover Date. 相似文献
15.
An ephemeris has been obtained for Explorer 28 (IMP 3) which agrees well with 2 years of radio observations and with SAO observations a year later. This ephemeris is generated over the 3 year lifetime by a numerical integration method utilizing a set of initial conditions, at launch and without requiring further differential correction. Because highly eccentric orbits are difficult to compute with acceptable accuracy and because a long continuous arc has been obtained which compares with actual data to a known precision, this ephemeris may be used as a standard for computing highly eccentric orbits in the Earth-Moon system.Orbit improvement was used to obtain the initial conditions which generated the ephemeris. This improvement was based on correcting the energy by adjusting the semimajor axis to match computed times of perigee passage with the observed. This procedure may generate errors in semimajor axis to compensate for model errors in the energy; however this compensation error is also implicit in orbit determination itself. 相似文献
16.
With the precise GPS ephemeris and clock error available, the iono- spheric delay is left as the dominant error source in the single-frequency GPS data. Thus, the removal of ionospheric effects is a ma jor prerequisite for an improved orbit reconstruction of LEO satellites based on the single-frequency GPS data. In this paper, the use of Global Ionospheric Maps (GIM) in kine- matic and dynamic orbit determinations for LEO satellites with single-frequency GPS pseudorange measurements is discussed first, and then, estimating the iono- spheric scale factor to remove the ionospheric effects from the C/A-code pseu- dorange measurements for both kinematic and dynamic orbit determinations is addressed. As it is known that the ionospheric delay of space-borne GPS sig- nals is strongly dependent on the orbit altitudes of LEO satellites, we select the real C/A-code pseudorange measurement data of the CHAMP, GRACE, TerraSAR-X and SAC-C satellites with altitudes between 300 km and 800 km as sample data in this paper. It is demonstrated that the approach to eliminating ionospheric effects in C/A-code pseudorange measurements by estimating the ionospheric scale factor is highly effective. Employing this approach, the accu- racy of both kinematic and dynamic orbits can be improved notably. Among those five LEO satellites, CHAMP with the lowest orbit altitude has the most remarkable improvements in orbit accuracy, which are 55.6% and 47.6% for kine- matic and dynamic orbits, respectively. SAC-C with the highest orbit altitude has the least improvements in orbit accuracy accordingly, which are 47.8% and 38.2%, respectively. 相似文献