Satellite Clock Error and Orbital Solution Error Estimation for Precise Navigation Applications

Global Positioning System (GPS) is a satellite-based navigation system that provides a three-dimensional user position (x,y,z), velocity and time anywhere on or above the earth surface. The satellite-based position accuracy is affected by several factors such as satellite clock error, propagation path delays and receiver noise due to which the GPS does not meet the requirements of critical navigation applications such as missile navigation and category I/II/III aircraft landings. This paper emphasizes on modelling the satellite clock error and orbital solution (satellite position) error considering the signal emission time. The transmission time sent by each satellite in broadcast ephemerides is not accurate. This has to be corrected in order to obtain correct satellite position and in turn a precise receiver position. Signal transmission time or broadcast time from satellite antenna phase center is computed at the receiver using several parameters such as signal reception time, propagation time, pseudorange observed and satellite clock error correction parameters. This corrected time of transmission and broadcast orbital parameters are used for estimation of the orbital solution. The estimated orbital solution was validated with the precise ephemerides which are estimated by Jet Propulsion Laboratory (JPL), USA. The errors are estimated for a typical day data collected on 11th March 2011 from dual frequency GPS receiver located at Department of Electronics and Communication Engineering, Andhra University College of Engineering, Visakhapatnam (17.73°N/83.319°E).

J_2 invariant relative orbits via differential correction algorithm

This paper describes a practical method for finding the invariant orbits in Ja relative dynamics. Working with the Hamiltonian model of the relative motion including the J2 perturbation, the effective differential correction algorithm for finding periodic orbits in three-body problem is extended to formation flying of Earth＇s orbiters. Rather than using orbital elements, the analysis is done directly in physical space, which makes a direct connection with physical requirements. The asymptotic behavior of the invariant orbit is indicated by its stable and unstable manifolds. The period of the relative orbits is proved numerically to be slightly different from the ascending node period of the leader satellite, and a preliminary explanation for this phenomenon is presented. Then the compatibility between J2 invariant orbit and desired relative geometry is considered, and the design procedure for the initial values of the compatible configuration is proposed. The influences of measure errors on the invariant orbit are also investigated by the Monte-Carlo simulation.

Consistency of MGEX Orbit and Clock Products

The analysis centers of the Multi-GNSS Pilot Project of the International GNSS Service provide orbit and clock products for the global navigation satellite systems(GNSSs)Global Positioning System(GPS),GLONASS,Galileo,and BeiDou,as well as for the Japanese regional Quasi-Zenith Satellite System(QZSS).Due to improved solar radiation pressure modeling and other more sophisticated models,the consistency of these products has improved in recent years.The current orbit consistency between different analysis centers is on the level of a few centimeters for GPS,around one decimeter for GLONASS and Galileo,a few decimeters for BeiDou-2,and several decimeters for QZSS.The clock consistency is about 2 cm for GPS,5 cm for GLONASS and Galileo,and 10 cm for BeiDou-2.In terms of carrier phase modeling error for precise point positioning,the various products exhibit consistencies of 2–3 cm for GPS,6–14 cm for GLONASS,3–10 cm for Galileo,and 10–17 cm for BeiDou-2.

High density porous polyethylene material (Medpor) as an unwrapped orbital implant

Objective: To introduce the clinical effect among patients who received an unwrapped orbital implant with high density porous polyethylene material (Medpor) after enucleation or evisceration. Methods: Retrospective analysis of a series of 302 patients with anophthalmia who underwent placement of an unwrapped high density porous polyethylene orbital implant. We compared the patients (n=180) who accepted primary implant placement with those (n=122) who accepted secondary implant placement. Parameters evaluated included: age at time of surgery, date of surgery, sex, implant type and size, surgery type, the surgical procedure and technique performed, and complications. Results: The time of follow-up ranged from 2.0 to 58.0 months (mean 32.5 months). A total of 5 of 302 (1.66%) cases had documented postoperative complications. The following problems were noted after surgery: implant exposure, 3 patients (0.99%); implant removed due to orbital infection, 1 patient (0.34%); ptosis, 1 patient (0.34%). There were no significant complications observed in other 297 cases and all implants showed good orbital mo- tility. The clinical effect of primary implant placement is better than that of secondary placement. Conclusion: High density porous polyethylene material can be used successfully as an unwrapped orbital implant in anopthalmic socket surgery with minimal complications. The material is well tolerated, nonantigenic and has low rate of infection and migration.

Characterizing receiver clock behaviors onboard Low Earth Orbiters:A case study of GRACE satellites

Accurate estimation of clocks, for example for the Gravity Recovery And Climate Experiment(GRACE)twin-satellites, is a critical part of precise orbit determination(POD) that ensures temporal gravity inversion. Characterizing the periodic variations of the receiver clocks is critical for precise clock modeling and prediction. In this study, the receiver clock is estimated using two different POD procedure: kinematic and reduced-dynamic approaches. Choices and the number of orbital parameters estimated in POD process affect the clock estimates, e.g., there are 8895 and 34,560 total parameters in the reduced-dynamic and kinematic approaches, respectively. In the both cases, the periodic variations of GRACE receiver clock are mainly dominated by the GPS orbit period, as well as once-(1-pr) and twiceper-revolution(2-pr) effects. Here the 1-pr effect is coupled with the relativistic effect, resulting in a difficulty to separate both signals. The clock amplitudes caused by the GPS orbit period, 1-pr and 2-pr are about 0.1, 0.03 and 0.01 ns, respectively. The GPS orbit period is almost one order magnitude larger than the 1-and 2-pr effect. The 0.1-ns amplitude of the 12-h periodic variation is equivalent to a 3-cm error in range. Such a systematic error should be considered in the receiver clock modeling for both the improvement of positioning accuracy and the reduction of number of unknown parameters, if the precise point positioning(PPP) technique is used for the orbit determination of the GRACE.

Exploring the effect of aggregation-induced emission on the excited state intramolecular proton transfer for a bis-imine derivative by quantum mechanics and our own n-layered integrated molecular orbital and molecular mechanics calculations

We theoretically investigate the excited state intramolecular proton transfer(ESIPT) behavior of the novel fluorophore bis-imine derivative molecule HNP which was designed based on the intersection of 1-(hydrazonomethyl)-naphthalene-2-ol and 1-pyrenecarboxaldehyde. Especially, the density functional theory(DFT) and time-dependent density functional theory(TDDFT) methods for HNP monomer are introduced. Moreover, the "our own n-layered integrated molecular orbital and molecular mechanics"(ONIOM) method(TDDFT:universal force field(UFF)) is used to reveal the aggregation-induced emission(AIE) effect on the ESIPT process for HNP in crystal. Our results confirm that the ESIPT process happens upon the photoexcitation for the HNP monomer and HNP in crystal, which is distinctly monitored by the optimized geometric structures and the potential energy curves. In addition, the results of potential energy curves reveal that the ESIPT process in HNP will be promoted by the AIE effect. Furthermore, the highest occupied molecular orbital(HOMO) and lowest unoccupied molecular orbital(LUMO) for the HNP monomer and HNP in crystal have been calculated. The calculation demonstrates that the electron density decrease of proton donor caused by excitation promotes the ESIPT process. In addition, we find that the variation of atomic dipole moment corrected Hirshfeld population(ADCH) charge for proton acceptor induced by the AIE effect facilitates the ESIPT process. The results will be expected to deepen the understanding of ESIPT dynamics for luminophore under the AIE effect and provide insight into future design of high-efficient AIE compounds.

6-3 Closed Orbit Correction in Electron Cooler Section at CSRe

The injecting section and the cooler section are apart from each other at CSRm, while the electron cooler systemis installed at the injecting section of CSRe[1]. So for the CSRe we not only need to satisfy the beam injectingcondition but also need to satisfy the beam cooling condition. At present, we use the ramping bump and the kickerto inject beam, and after injection the bump disappear quickly and the beam goes to the cooling orbit and begincooling. This method has a disadvantage that the beam cooling condition cannot be satised until the bump isdown. In the past year, we try to nd a new method to correct the orbit of cooler section. Instead of using rampingbump we use the xed bump to satisfy the injecting and the cooling condition at the same time.

红外高光谱大气探测仪(FY-3E/HIRAS-Ⅱ)在轨数据非线性校正方法

风云三号E星(FY-3E)搭载的高光谱大气探测仪(HIRAS-Ⅱ)能够实现大气的垂直探测,具有高光谱、高灵敏度、高精度的特点。仪器在轨之后由于仪器衰减和环境变化的原因产生非线性响应,影响在轨定标精度。针对非线性响应的问题,提出了一种基于带内光谱的非线性校正方法。首先基于带外低频光谱的非线性特征求解非线性校正系数,将此系数作为初值输入到辐射定标模型中,以星上测量的黑体带内光谱与理想光谱的偏差为目标函数,通过迭代优化非线性校正系数。通过辐射定标实验得出,校正后的黑体亮温偏差明显低于未校正和基于带外光谱的校正方法。将HIRAS-Ⅱ的观测数据与IASI进行交叉比对并计算平均亮温偏差和偏差绝对值,经过带内校正法非线性校正后的亮温平均偏差为-0.13 K,优于带外校正方法。

地月周期轨道对地月L1与L2附近Halo轨道的可见性分析

随着去往月球航天器的增多,现有的近地空间光学卫星与地基光学望远镜的探测能力已无法满足要求,急需增强地月空间观测能力,通过使用地月周期轨道来填补地月空间观测能力的不足被认为是一种有效手段。针对地月周期轨道的特性,文章基于微分校正原理对三体轨道建模,并完成了算法的设计,提出了地月周期轨道的选择原则,并优选了3条轨道。在地月周期轨道对地月拉格朗日点L1、L2附近Halo轨道的可见性分析中,为方便评估,采用类球体的物体星等评估模型来定义可见性的评估标准;基于卫星工具包提供模型计算中涉及的自然天体、物体和观测卫星三者的时空关系,给出了可见性分析过程及结果,研究表明地月周期轨道对地月拉格朗日点L1、L2附近Halo轨道均有不错的观测效果,其中轨道1对地月周期轨道的可见性综合最高,均大于95%。

顾及BDS-3星钟约束的GNSS超快速轨道钟差解算方法

BDS-3高稳定星载原子钟作为北斗星座的显著技术优势,在GNSS数据处理中尚未得到充分利用。针对严格时效性限制下GNSS超快速轨道钟差参数精度受限问题,本文提出顾及BDS-3星钟约束的GNSS超快速轨道钟差解算方法。首先,以GNSS轨道钟差参数间相关性为基础,构建顾及BDS-3星钟参数特性的GNSS定轨模型;然后,基于GNSS精密钟差产品,分析星钟约束对GNSS轨道钟差参数精度的影响规律;最后,为克服预报钟差精度与约束筛选对定轨影响,建立BDS-3星钟建模与GNSS超快速轨道钟差估计的同步处理方法。试验结果表明,在BDS-3星钟参数最优约束下,BDS-3与GPS轨道钟差精度可分别提升27.5%、5.1%和20.2%、5.2%;且较传统BDS-3星钟单历元处理策略,基于BDS-3星钟建模与GNSS超快速定轨同步处理方法,GNSS超快速轨道钟差精度可分别提升至4.8%与34.2%,轨道精度实现了毫米级改善。因此,顾及BDS-3星钟约束的GNSS超快速轨道钟差解算方法可有效对BDS-3高稳星钟信息模型化,并实现GNSS超快速轨道钟差精度的优化处理。

面向导航增强的低轨卫星钟差确定及预报方法研究

低轨导航增强是未来导航发展的重要趋势,而高精度低轨卫星钟差是实现低轨导航增强的必要条件。基于Sentinel-6A卫星,对低轨卫星钟差特性进行了分析,给出了钟差确定方法及影响因素,介绍了顾及钟差特性的低轨卫星钟差预报方法。实验表明,低轨卫星钟差含有多个周期项,给低轨卫星建模和预报带来了困难。与使用运动学定轨模型相比,基于简化动力学的定轨模型可显著提升低轨卫星钟差精度;当基于运动学模型确定低轨卫星钟差时,相较于使用GPS单系统数据,多GNSS观测数据可提升低轨卫星钟差精度。研究表明,基于GPS和Galileo观测的Sen-tinel-6A卫星钟差精度相较于GPS单系统钟差精度改善了36%,同时,所使用的GNSS产品精度与低轨卫星钟差精度密切相关。利用顾及卫星钟差特性的低轨卫星钟差预报方法,当预报时长小于1min,低轨卫星钟差预报精度(预报与解算值之差的RMSE)在0.1ns之内,当预报时长小于5min,预报精度在0.3ns之内,随着预报时长的增长,预报精度显著下降。

手术治疗眼球摘除术后结膜囊畸形的下睑外翻

目的:回顾分析治疗眼球摘除术后结膜囊畸形的下睑外翻这类手术的关键技术。方法:回顾性分析2015年3月-2017年12月在笔者医院接受手术治疗的眼球摘除术后结膜囊畸形的下睑外翻患者8例(8只眼),所有患者仅行针对结膜囊畸形的手术矫正,而未采取针对下睑外翻常用的下睑全层楔形切除、外侧睑板条锚定、皮瓣法等术式。结果:8例患者均单纯行二期义眼台植入+结膜囊成形术并穹窿部弧形压管获得了深在、稳定的结膜囊,佩戴义眼片后,下睑缘位置满意,无内外翻。在无需接受任何下睑外翻矫正措施的情况下获得了满意的下睑形态及功能。结论:眼球摘除术后结膜囊畸形的下睑外翻手术关键点在于矫正眼眶凹陷,恢复结膜囊正常形态,尤其是加深下穹窿。

采用北斗PPP-B2b服务的大气可降水量反演及香港地区暴雨过程分析

北斗三号卫星导航系统精密单点定位服务(PPP-B2b服务)通过卫星B2b信号向用户发送改正信息,摆脱了对外部通信的依赖,为实时反演大气可降水量(PWV)提供了新的技术途径。本文利用试验分析了PPP-B2b服务反演PWV的精度。试验结果表明,利用PPP-B2b服务反演结果与采用CODE事后精密星历产品的差值RMS为3.70 mm,STD为3.61 mm,与ERA5再分析数据差值的RMS和STD分别为4.80和4.07 mm,与探空结果差值的RMS和STD分别为3.75和7.16 mm,验证了采用PPP-B2b服务的PWV反演结果具有较好的精度。最后,通过分析香港地区暴雨过程的实际降水量与PWV反演结果之间的相关性,初步验证了BDS PPP-B2b服务用于暴雨灾害短时预警的可行性。

不同IGS分析中心BDS-3实时精密轨道和钟差产品精度评估

以2022-11连续7 d的精密星历作为参考,对5家机构(CAS、CNES、GFZ、SHA和WHU)提供的BDS-3实时精密产品进行精度评估。结果表明,目前CAS可提供的BDS-3卫星实时精密产品数量最多,但MEO卫星钟差精度最低,超过0.4 ns;GFZ播发的IGSO卫星产品质量最差,径向轨道误差超过30 cm,钟差精度大于0.8 ns;WHU的产品数据质量最好,径向轨道误差优于4 cm,钟差精度约0.16 ns,但其可用卫星数仅19颗。在定位端,对各机构的实时精密产品进行双频无电离层动态实时PPP定位性能对比,结果显示,CNES、SHA、WHU实时产品定位精度处于同一水平,水平、高程方向总体定位误差约为0.2 m。综合考虑可用卫星数及实时产品数据质量,推荐实时PPP用户使用CNES或SHA实时产品。

BDS-3卫星钟差改正数短期预报方法研究

针对RTS实时数据流产品在网络传输中存在的延迟以及数据中断等问题,文中结合BDS-3卫星钟差改正数的特点,分析实时数据流中BDS-3卫星钟差改正数的完整率和精度,提出一种基于一次差分和滑动时间窗口的残差修正钟差改正数短期预报模型。利用文中模型与一次多项式模型、基于一次差分的一次多项式模型和灰色模型进行BDS-3卫星钟差改正数预报精度的对比实验,结果表明,文中模型的预报精度最高,5 min、10 min、15 min和20 min的平均预报精度分别达到0.12 ns、0.14 ns、0.19 ns和0.20 ns,有效降低误差累积效应对预报精度的影响,对于RT-PPP的研究和应用具有重要的意义。

GPS/Galileo/BDS-3广播星历精度分析

为了分析当前GPS(Global Positioning System)、Galileo(Galileo Navigation Satellite System)和BDS-3(Beidou Navigation Satellite System with Global Coverage)广播星历的精度,详细分析研究了各种偏差改正及消除方法,并尽可能地消除了系统误差和粗差对评估结果的影响。选取2021-11-01/12-31共61天MGEX(multi-GNSS experiment)发布的多系统混合广播星历与武汉大学分析中心发布的事后精密星历数据进行实验,对GPS、Galileo和BDS-3近期广播星历精度进行对比分析,实验结果表明:3个系统广播星历整体精度由高到低依次是Galileo、BDS-3和GPS,其空间信号测距误差的RMS(root mean square)分别优于0.17、0.25和0.37 m,整体轨道精度的RMS分别优于0.17、0.12和0.25 m,BDS-3广播星历的轨道精度最高,钟差误差的RMS分别优于0.15、0.23和0.27 m,Galileo广播星历的钟差精度最高。对于GPS卫星的广播星历,blockⅢA卫星钟差和轨道精度均优于其他GPS类型卫星。

基于OTN技术的电力光通信网络延时误码修正技术

为了保证电力大数据的完整和安全传输,并保证该数据的传输时效性,研究基于OTN技术的电力光通信网络延时误码修正技术。分析电力光通信网络中的延时和误码特性,结合分析结果和电力企业对光通信网络的传输需求,采用OTN技术优化电力光通信网络,保证电力大数据的传输可靠性。测试结果显示:混频效应指标结果均高于0.922,误码率指标均低于0.0085%;主、从时钟的最大偏差和平均偏差结果最大值分别为0.0031 ms和0.0007 ms;接收端风险均衡度和接收业务风险度的最高值分别为3.4%和1.05%,保证电力大数据传输时效性和完整性。

Anomalous Hall Effect in Spin-Polarized Two-Dimensional Hole Gas with Cubic-Rashbsa Spin-Orbit Interaction

Based on the Kubo formalism,the anomalous Hall effect in a magnetic two-dimensional hole gas withcubic-Rashba spin-orbit coupling is studied in the presence of 5-function scattering potential.When the weak,short-rangeddisorder scattering is considered in the Born approximation,we find that the self-energy becomes diagonal inthe helicity basis and its value is independent of the wave number,and the vertex correction to the anomalous Hallconductivity due to impurity scattering vanishes when both subbands are occupied.That is to say,the anomalous Halleffect is not vanishing or influenced by the vertex correction for two-dimensional heavy-hole system,which is in sharpcontrast to the case of linear-Rashba spin-orbit coupling in the electron band when the short-range disorder scattering isconsidered and the extrinsic mechanism as well as the effect of external electric field on the SO interaction are ignored.

BDS实时精密单点定位性能分析

以GFZ事后精密轨道与钟差产品为参考,评估CNES实时轨道与钟差精度。基于CNES实时轨道和钟差,对18个MGEX地面站进行了实时精密单点定位(Real-Time Precise Point Positioning, RT PPP)测试,以GPS为参考分别对比分析了BDS3、BDS2+3的RT PPP的性能。结果表明,GPS实时轨道三维精度优于11 cm,实时钟差精度约为0.02~0.06 ns, BDS非GEO卫星实时轨道三维精度优于33 cm,钟差精度约为0.05~0.29 ns。BDS与GPS三维定位精度基本相当,约为5~6 cm。GPS平均收敛速度约为59 min, BDS平均收敛时间约为124 min。相对于BDS3、BDS2+3在E、N、U三方向的定位精度分别提升9.9%、6.7%、2.6%,3D定位精度提升5.8%,收敛速度提升20.2%。

BDS-3卫星钟在轨性能评估与分析

目前,国际主要卫星导航系统搭载的原子钟包含铷钟、氢钟、铯钟3大类。新型国产星载铷原子钟、氢原子钟的应用是BDS-3相对于BDS-2的重要改变之一。BDS-3正式开通运行以来,已经积累了丰富的在轨数据,本文采用2 a的精密钟差数据评估了新型国产原子钟的在轨性能,并与国际主流星载原子钟的性能进行对比,分析了国产原子钟在轨长期演化规律。结果表明,北斗氢钟具有较低的在轨漂移率和较高的稳定度,与Galileo系统星载氢钟为同一精度水平,北斗铷钟在轨性能稳步提高,跻身世界先进行列。