单颗LEO卫星轨道参数对GPS掩星事件分布和数量影响的模拟研究

针对利用LEO星载GPS接收机对GPS卫星进行掩星观测的任务,在建立LEO卫星轨道模拟系统的基础上,考虑卫星几何关系和天线视场的情况下,对掩星事件进行了模拟。分析了对于单颗LEO卫星,掩星事件的分布和数量随着LEO轨道参数包括轨道升交角距、升交点赤经、轨道高度和倾角而变化的规律,并得出了相应结论。     

联合GNSS/LEO卫星观测数据的区域电离层建模与精度评估

高精度的电离层模型对于提高导航卫星系统的定位精度具有重要意义。低轨卫星的快速发展为建立高精度的电离层模型提供了新的契机。基于仿真数据模拟获得2017年1月1日—30日LEO(low earth orbit)和GNSS(global navigation satellite system)卫星观测数据,星座类型包括60、96、192和288颗卫星,以非洲区域为例,利用该数据研究GNSS和LEO卫星穿刺点的覆盖情况和联合建模精度。结果表明:加入LEO卫星后,穿刺点分布改善明显,能够大幅度提高穿刺点密度;单颗低轨卫星穿刺点的范围比GNSS卫星大,LEO卫星的高度角和方位角变化明显;随着低轨卫星数量的增加,融合建模的精度也随之提高;在12:00时东经30°不同纬度范围内,单GNSS建模和GNSS+288 LEO建模差值最大为-1.6 TECU(total electron content unit);随着建模时长的增加,融合建模结果和单GNSS结果差值逐渐变小。     

不同反射天线覆盖和安装条件下星载GNSS?R关键参数的仿真分析

以风云三号（Fengyun 3, FY3）E星（FY3E）全球导航卫星系统(global navigation satellite system, GNSS)掩星探测仪Ⅱ型(the Ⅱ generation of GNSS occultation sounder, GNOSⅡ)的星载GNSS的反射信号(GNSS reflectometry, GNSS-R)遥感场景为例,使用GNSS-R端到端性能模拟器软件,在不同反射天线覆盖（即不同天线波束宽度）和不同安装条件（包括安装天线法向不同的倾斜角度和倾斜方向）下,对可观测镜面反射点(specular point, SP)平均数量、SP最大数量、平均路径损耗、近地轨道(low Earth orbit, LEO)处反射信号入射角和SP处反射信号反射角等物理参量进行了仿真模拟,分析了各GNSS-R仿真参量与天线倾斜角度、倾斜方向和波束宽度之间的数值变化关系;并结合雪花图方法,进行了整体视角的分析。结果表明,天线波束宽度对各仿真参量的影响最大,倾斜角度次之,倾斜方向的影响最小,且天线波束宽度与SP数量成正比,与能量损耗成反比,天线设计需考虑各影响因素的平衡。     

利用GNSS-R信号进行交通车流检测

为了有效检测交通状况,提出了一种使用GNSS-R （导航卫星反射）信号进行车流检测的方法。该方法利用两种天线分别接收导航卫星直射信号和反射信号,使用通用接收机进行信号采集后,在软件接收机中进行信号处理解算,获得直射通道和反射通道的相关功率,以及卫星的高度角。然后使用反演介电常数的方法对车辆进行探测,获得交通车流状况。通过试验验证,该方法能够有效地对探测区域内的车辆进行检测,证明了使用GNSS-R进行交通车流检测的可行性。     

利用卫星星座对GNSS-R海洋遥感时空特性进行研究

利用仿真方法研究了GNSS-R接收天线俯仰角、卫星轨道长半轴和轨道倾角对镜像反射点数量的影响,对4颗和6颗卫星组成的星座时空分辨率进行了仿真计算,分别获取了星座的时间分辨率。认为由6颗卫星组成的星座,8 h可完成全球5°×5°海洋格点的探测任务。     

低轨卫星增强北斗三号导航星座性能分析

针对低轨卫星星座有待合理化设计的问题,深入研究了低轨卫星星座增强北斗三号系统定位性能。分析轨道高度、轨道倾角、星座构型对星座覆盖性能的影响,仿真北斗三号、GPS和3种不同类型的低轨星座,研究各低轨星座与北斗三号、GPS的组合系统在所选7个测站以及全球范围内的可见卫星数和PDOP值分布。结果表明低轨卫星对北斗三号的增强效果主要与低轨卫星数目有关,且不同轨道倾角的组合低轨星座有利于均衡系统在全球范围内的可见卫星数与PDOP值分布。低轨卫星有望通过改善卫星观测几何构型提高北斗三号系统的定位性能,且增强效果与低轨星座构型密切相关。     

LEO星座参数对GPS掩星数量和时空分布影响的模拟研究

利用低地球轨道LEO(Low Earth Orbit)卫星上的星载接收机对GPS卫星进行掩星观测反演地球的大气性质,对于气象学和大气研究具有重要意义.与单颗LEO卫星相比,由多个卫星组成的LEO星座观测到的掩星事件在时空分辨率和数量上都有很大的提高.考虑特定的区域,采用数值模拟方法,对不同卫星数和不同星座参数k的玫瑰型星座在一天内所观测的掩星事件的数量和分布进行比较分析,得到相应结论.研究成果对实际发射LEO星座时相关参数的选取具有参考价值.     

区域监测站与低轨卫星数据联合测定MEO卫星轨道

我国北斗二代系统(BDS)地面运控监测站数量较少且为区域分布,短期内难以实现全球建站,因此对全球运行的中圆地球轨道卫星(MEO)难以形成连续多重覆盖观测,导致BDS的MEO实时轨道精度偏低。基于上述问题,本文考虑到低轨卫星星载GNSS数据可以有效弥补区域监测站在空间覆盖及几何结构上的不足,设计了一种将星载GNSS接收机作为高动态天基监测站,联合地面区域监测站数据对卫星导航系统的MEO卫星轨道进行实时解算预报的方法。算例结果显示:7个区域监测站联合1至3个天基监测站,其定轨精度可分别提升约21%、34%和55%,这也表明,地面区域监测站联合天基低轨卫星数据可有效提高MEO卫星的轨道精度。建议我国BDS在区域测站分布阶段可采用联合低轨卫星数据方法提高北斗MEO卫星实时轨道精度。     

低轨导航增强卫星的轨道状态型星历参数设计

导航增强卫星从高轨拓展到低轨,需要设计可靠的低轨道LEO广播星历参数。GLONASS广播星历模型能够利用9个状态参数高精度描述30min内中高轨卫星的摄动运动,但不能直接用于低轨卫星。为了适应LEO的摄动力的短期快变化,设计了基于轨道状态型的21参数广播星历模型。分析了低轨卫星主要摄动力的短期变化规律,选取了二次多项式和基于轨道半周期的三角函数来补偿大气阻力等主要摄动在3个方向上的累计。基于星历拟合试验讨论了拟合参数个数、拟合时段和数据间隔对500~1200km轨道高度的LEO圆轨道的拟合精度影响。试验表明,当拟合时段为20min(约1/5个轨道周期)时,轨道高度大于700km的近圆轨道,拟合用户距离误差(FURE)精度优于0.05m;高度为1000km时,FURE平均精度达到0.03m。     

面向精密位置服务的低轨卫星轨道预报精度分析EI北大核心CSCD

LEO卫星精密轨道预报是LEO导航增强系统中重要的技术环节之一,本文使用多种算法来实现不同任务需求下的轨道预报。对于在地面处理系统实现的LEO轨道预报,算法1采用定轨预报同时处理的策略,算法2将离散轨道点进行动力学拟合再进行积分外推。GRACE-C卫星预报5、10、15 min的URE平均精度分别为5.25、5.67、6.25 cm;HY2A卫星为7.83、8.69、9.66 cm;SWARM-A卫星为8.88、9.22、9.63 cm;SWARM-B卫星为8.49、8.98、9.63 cm。对于计算条件受限的LEO星上轨道预报,本文利用单个轨道点及简单动力学模型进行轨道积分外推的算法。该算法主要考虑地球中心引力及非球形引力摄动,因此地球重力场阶次对轨道预报精度产生较大影响。平均高度为500 km的LEO卫星选取60阶重力场,高度为1000 km的LEO卫星选取30阶重力场,可实现预报10 min轨道优于10 cm的预报精度。     

Simulation of the impacts of single LEO satellite orbit parameters on the distribution and number of occultation events

Focusing on carrying out GPS occulatation observations with a receiver set on LEO satellite, this paper develops the LEO orbit simulation system based on which the occultation events can be simulated taking into account the geometric relationship of the satellites and the field of view of the receiver antenna. In this paper, the impacts of 4 types of LEO orbit parameters including argument of latitude (AOL), right ascension of ascending node (RAAN), orbit height and orbit inclination on the distribution and number of occultation events observed with a single LEO satellite are discussed through simulation and some conclusions are drawn.     

Simulation of the impacts of single LEO satellite orbit parameters on the distribution and number of occultation events

Introduction WithGPSreceiversmountedonLEOsatel lites,GPSoccultationeventscanbeobserved.Theobservablesarevaluableforatmospheric monitoringandweatherforecasting.Whenpre paringtobuildupanLEOsatelliteoccultation observationsystem,theevaluation,designand imple…     

两种GNSS-R镜面反射点搜索算法

全球卫星导航系统反射(GNSS-R)技术对海洋表面地形精确信息的提取和研究具有重要意义,针对镜点搜索的精度需求,本文提出2种镜面反射点搜索算法. 首先,在分析基本反射关系的基础上,提出一种基于斐波那契法的搜索算法,并从数论的角度证明其相对黄金分割法的优越性. 其次,提出一种基于极值求导的做法,[JP2]建立变量K的距离和函数,这种做法省略了传统做法中的不断迭代过程. 最后,通过导航模拟器生成全球卫星导航系统（GNSS）卫星和接收机坐标,并利用MATLAB进行仿真. 仿真结果表明,斐波那契法相较黄金分割有一定的提升,极值求导做法能够计算出镜面反射点的位置信息,并且摒弃了传统的不断迭代步骤.      

低轨道卫星重复周期的设计方法及其对重力场反演的影响

研究低轨卫星重复周期的设计原理,给出相应的计算公式。基于此对不同轨道高度卫星的重复周期进行数值仿真,并利用动力学方法分析不同重复周期轨道星下点轨迹的空间采样对重力场反演精度的影响。结果表明,卫星的重复周期与其轨道高度的变化并不成线性关系,并且在顾及重力场时间分辨率的情况下,长重复周期能够提高卫星地面轨迹的空间采样,为重力场解算提供较好的条件。     

Phase center modeling for LEO GPS receiver antennas and its impact on precise orbit determination

Most satellites in a low-Earth orbit (LEO) with demanding requirements on precise orbit determination (POD) are equipped with on-board receivers to collect the observations from Global Navigation Satellite systems (GNSS), such as the Global Positioning System (GPS). Limiting factors for LEO POD are nowadays mainly encountered with the modeling of the carrier phase observations, where a precise knowledge of the phase center location of the GNSS antennas is a prerequisite for high-precision orbit analyses. Since 5 November 2006 (GPS week 1400), absolute instead of relative values for the phase center location of GNSS receiver and transmitter antennas are adopted in the processing standards of the International GNSS Service (IGS). The absolute phase center modeling is based on robot calibrations for a number of terrestrial receiver antennas, whereas compatible antenna models were subsequently derived for the remaining terrestrial receiver antennas by conversion (from relative corrections), and for the GNSS transmitter antennas by estimation. However, consistent receiver antenna models for space missions such as GRACE and TerraSAR-X, which are equipped with non-geodetic receiver antennas, are only available since a short time from robot calibrations. We use GPS data of the aforementioned LEOs of the year 2007 together with the absolute antenna modeling to assess the presently achieved accuracy from state-of-the-art reduced-dynamic LEO POD strategies for absolute and relative navigation. Near-field multipath and cross-talk with active GPS occultation antennas turn out to be important and significant sources for systematic carrier phase measurement errors that are encountered in the actual spacecraft environments. We assess different methodologies for the in-flight determination of empirical phase pattern corrections for LEO receiver antennas and discuss their impact on POD. By means of independent K-band measurements, we show that zero-difference GRACE orbits can be significantly improved from about 10 to 6 mm K-band standard deviation when taking empirical phase corrections into account, and assess the impact of the corrections on precise baseline estimates and further applications such as gravity field recovery from kinematic LEO positions.     

Precise orbit determination for the GRACE mission using only GPS data

The GRACE (gravity recovery and climate experiment) satellites, launched in March 2002, are each equipped with a BlackJack GPS onboard receiver for precise orbit determination and gravity field recovery. Since launch, there have been significant improvements in the background force models used for satellite orbit determination, most notably the model for the geopotential. This has resulted in significant improvements to orbit accuracy for very low altitude satellites. The purpose of this paper is to investigate how well the orbits of the GRACE satellites (about 470 km in altitude) can currently be determined using only GPS data and based on the current models and methods. The orbit accuracy is assessed using a number of tests, which include analysis of orbit fits, orbit overlaps, orbit connecting points, satellite Laser ranging residuals and K-band ranging (KBR) residuals. We show that 1-cm radial orbit accuracy for the GRACE satellites has probably been achieved. These precise GRACE orbits can be used for such purposes as improving gravity recovery from the GRACE KBR data and for atmospheric profiling, and they demonstrate the quality of the background force models being used.