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1.
激光跟踪仪动态精度评定方法研究 总被引：1，自引：0，他引：1
激光跟踪仪采用激光干涉测距和动态度盘测角,单次测量时间为1/3000 s,可对空间运动目标进行跟踪并测量其空间三维坐标,具有测量速度快、测量精度高、测量范围广等优点。本文在对激光跟踪仪动态跟踪原理及检校方法进行理论分析的基础上,依据激光跟踪三维坐标测量系统校准规范,利用最小二乘原理对空间所形成的圆平面进行了拟合解算,采用统计分析的方法对激光跟踪仪的动态精度评定进行了比较深入的研究;以Leica AT901-B激光跟踪仪为例,借助球杆装置,对激光跟踪仪的动态性能进行了测试。 相似文献
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本简述了在道路施工测量中采用随机放样方法的必要性和适用性，可将其作为常规放样方法的一种补充。在道路坐标系统下对于各种曲线线形的随机放样的原理和方法作了详细的解析，并基于缓和曲线及其平行线以其自身弧长为变量的参数方程，提出了在缓和曲线范围内实现随机放样的严密算法，较好地解决了自动解算问题。为编制通用的模块化程序提供参考。 相似文献
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激光跟踪仪在激光干涉测距模式下,其测距精度要远远高于测角精度,利用极坐标测量的空间点坐标精度主要受测角误差的影响,利用激光跟踪仪的高精度激光干涉测距值构成空间三维激光干涉测边网,消除测角误差对空间点位的影响,采用基于重心基准的加权秩亏网平差模型进行整网平差。定向点坐标近似值采用极坐标方法确定,测站中心坐标近似值采用距离后方交会解算,通过附加约束矩阵精密求解测站点和定向点的三维坐标值。实际计算结果表明,该模型在12m测量范围内将激光跟踪仪的点位精度由87μm(标称值)提高到了27μm。 相似文献
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附非负约束平差模型的最小二乘估计 总被引：1，自引：1，他引：0
研究了不等式约束下的平差问题,即先将不等式约束的最小二乘问题转换成凸二次规划问题,然后求其最优解.给出了几个判定最优解的充分必要条件,以及非负约束下的平差问题参数最小二乘估计的一般形式,并给出了简明的算法.模拟实例说明,此算法可以很好地应用于实际测量中的平差计算. 相似文献
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同波束干涉测量差分相位计算与DOR时延精度验证 总被引：1，自引：1，他引：0
同波束干涉测量可以获取多航天器间高精度相对角位置信息。但对于两航天器间匹配频点少、频点间频差大、观测非连续条件下如何获取高精度的相对角位置观测量仍然是一个尚待解决的问题。我国在嫦娥二号(CE-2)卫星上首次搭载了差分单程测距(DOR)信标,用于测量技术测试验证,如何对DOR信号带宽综合时延进行精度验证也是本文关心的问题。文中提出基于相位补偿的差分相位解算方法,并基于DOR多频点信号测量数据进行了方法验证。给出DOR带宽综合解算方法,分析DOR无模糊解算条件;通过合理设置采样通道,实现了由单通道群时延验证DOR带宽综合时延。嫦娥二号卫星实测数据分析表明,相位补偿法可以得到反映航天器间相对角位置的差分相位观测量;DOR带宽综合时延与单通道时延解算结果一致,且时延解算精度有显著提高。 相似文献
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首先，用贝叶斯（Bayes）统计理论的观点，把未知参数看作随机变量，引入未知参数的无信息先验分布函数，从数学上推导了均方误差最小意义下的正则化矩阵；然后，结合最优正则化矩阵和快速截断奇异值算法，提出了一种新的正则化方法；最后，探讨了新方法在全球卫星导航系统（Global Navigation Satellite System，GNSS）模糊度解算中的应用。通过一组GNSS模糊度解算实验，比较了最小二乘（least squares，LS）方法、L曲线岭估计和新方法的性能。结果表明，新方法解算成功率略高于L曲线岭估计，远高于LS方法；计算耗时略大于LS方法，远小于L曲线岭估计。 相似文献
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部分参数有非负约束平差模型的一种新算法 总被引：6，自引：1，他引：6
研究了部分参数带有非负约束的平差模型,提出了一种新的处理部分参数附有非负约束的平差方法。该方法是先将非负约束的最小二乘问题转换成凸二次规划问题,然后求其最优解。通过模拟实例说明,此算法可以很好地应用于实际测量中的平差计算。 相似文献
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介绍了天文方位角测量原理,给出了实用的计算太阳视位置的方法;研究了在白天恒星无法应用的情况下,利用电子经纬仪测日进行快速天文定向及方位角测量,给出了具体的实施方法及数据解算过程,并对实际测量数据进行了精度分析. 相似文献
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姿态模式切换期间QZSS卫星轨道及其钟差产品特性分析 总被引：1，自引：1，他引：0
导航卫星姿态控制模式切换对精密定轨解算得到的轨道和钟差均有较大影响。本文首先从理论上分析了卫星偏航姿态及其对精密定轨的影响,然后分别以卫星激光测距检核和钟差多项式拟合的方法对IGS MGEX分析中心的QZSS卫星轨道和钟差产品精度进行评价,最后以谱分析方法和改进阿伦方差揭示了卫星钟差的周期特性。基于2014年全年的QZSS卫星轨道和钟差产品的研究表明,一年内有两次长约20 d的地影季,太阳角呈现半年周期的波动;QZSS卫星在低太阳角时有零偏保护,其卫星轨道和钟差精度都与太阳角有显著相关性;卫星钟差具有与轨道周期相近的周期项,且周期项振幅与太阳角的大小也具有相关性,表明现有的定轨策略存在不足。考虑到QZSS与目前北斗星座中IGSO和MEO卫星姿态控制模式的相似性,该结论对于研究我国BDS姿态切换期间的精密定轨有一定参考价值。 相似文献
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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
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This study analyzes the quality of onboard data of tracking signals from GPS satellites on the far side of the earth and determines the orbit of the geostationary satellite using code and carrier phase observations with 30-h and 3-day orbit arc length. According to the analysis results, the onboard receiver can track 6–8 GPS satellites, and the minimum and maximum carrier to noise spectral densities were 24 and 45 dB-Hz, respectively. For a GPS receiver on a high-altitude platform above the navigation constellations, the blocking of the earth and a weak signal strength usually cause a piece-wise GPS signal tracking and an increase in the number of ambiguity parameters. Individual GPS satellites may be continuously tracked for as little as several minutes and as long as 3 h. Moreover, considering the negative sign of elevation angles reflects the fact that GPS satellites are tracked below the receiver in the study. GPS satellites appear mainly in the elevation angle range of ??53° to ??83°, and dilution of precision values could reach ten or one hundred and more. Also, it is observed that when a signal suffers from atmospheric refraction, other GPS signals tracked simultaneously by the receiver experience strong systematic errors in the code observations. Based on single-frequency code and carrier phase measurements, the mean 3D root mean square (RMS) value of the overlap comparisons between 30-h orbit determination arcs is 2.14 m. However, we found that there were also some biases in the carrier phase residuals, which contributed to poor orbit accuracy. To eliminate the effects of the biases, we established a correction sequence for each GPS satellite. After corrections, the mean 3D RMS was reduced to 0.99 m, representing a 53% improvement. 相似文献
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针对北斗GEO、IGSO、MEO的3种卫星类型和动态偏航、零偏航两种姿态控制模式,进行了以ECOM光压模型为基础的轨道预报精度分析。确定了北斗3类卫星的短期、中期、长期预报光压参数选择策略。采用光压参数修正法,通过对北斗卫星光压参数长期变化规律建模,有效提升了地影段轨道长期预报精度。研究结果可同时服务于北斗卫星轨道确定及历书参数生成。 相似文献
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High precision geodetic applications of the Global Positioning System (GPS) require highly precise ephemerides of the GPS satellites. An accurate model for the non-gravitational forces on the GPS satellites is a key to high quality GPS orbit determination, especially in long arcs. In this paper the effect of the satellite solar panel orientation error is investigated. These effects are approximated by empirical functions to model the satellite attitude variation in long arc orbit fit. Experiments show that major part of the long arc GPS orbit errors can be accommodated by introducing a periodic variation of the satellite solar panel orientation with respect to the satellite-Sun direction, the desired direction for solar panel normal vector, with an amplitude of about 1 degree and with a frequency of once per orbit revolution. 相似文献
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卫星自主定轨是提高全球卫星导航系统(GNSS)可靠性、稳健性、完整性和生存能力的重要保证。新一代的北斗卫星已可以进行星间链路测距,从而达到提高卫星全球跟踪能力以及实现整个卫星导航系统的自主定轨。然而由于卫星运行会受到多种摄动力的影响,如果不能对这些摄动力进行精密的改正,在没有地面或其他天体提供绝对约束的条件下,导航系统会随着自主定轨时间的延长出现星座整体旋转。卫星所受摄动力分为保守力和非保守力两部分:对于保守力,如地球非球形摄动、潮汐摄动、太阳月球和其他三体引力,现在已有的力学模型可以很精确地进行改正;而非保守力(如太阳光压摄动),则难以用精确的模型进行改正,因此成为影响卫星定轨精度的主要因素。星载加速度计可以高精度地测量非保守力,并已成功应用于重力卫星(CHAMP、GRACE、GOCE)的重力场反演与大气研究中。本文研究主要探讨采用星上加速度计提高北斗卫星自主定轨精度和延长自主定轨时长的可行性。利用模拟的卫星轨道和星间链路数据,以及现有的星载加速度计误差模型,对北斗卫星系统分别使用星间链路数据和星间链路与加速度计组合数据,进行自主定轨与精度评定。计算结果表明,使用星间链路与星载加速度计数据进行自主定轨,较单纯使用星间链路数据精度具有明显改进。在模拟的星间测距观测数据具有0.33m随机噪声以及分米级系统误差,自主定轨两个月的情况下,联合使用加速度计数据的自主定轨IGSO和MEO卫星精度为分米级,而仅使用星间链路数据的定轨精度约为3~6m,比使用加速度计精度低一个量级。 相似文献
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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
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Initial results of centralized autonomous orbit determination of the new-generation BDS satellites with inter-satellite link measurements 总被引：3，自引：0，他引：3
Chengpan Tang Xiaogong Hu Shanshi Zhou Li Liu Junyang Pan Liucheng Chen Rui Guo Lingfeng Zhu Guangming Hu Xiaojie Li Feng He Zhiqiao Chang 《Journal of Geodesy》2018,92(10):1155-1169
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. 相似文献
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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
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Krzysztof Sośnica Lars Prange Kamil Kaźmierski Grzegorz Bury Mateusz Drożdżewski Radosław Zajdel Tomasz Hadas 《Journal of Geodesy》2018,92(2):131-148
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. 相似文献