Precise orbit determination for Jason-1 satellite using on-board GPS data with cm-level accuracy

The joint US/French Jason-1 satellite altimeter mission, launched from the Vandenberg Air Force Base on December 7, 2001, continues the time series of centimeter-level ocean topography observations as the follow-on to the highly successful T/P radar altimeter satellite. Orbit error especially the radial orbit error is a major component in the overall budget of all altimeter satellite missions, in order to continue the T/P standard of observations. Jason-1 has a radial orbit error budget requirement of 2.5 cm. In this work, two cycles (December 19, 2002 to January 7, 2003) of the Jason-1 on-board GPS data were processed using the zero-difference (ZD) dynamic precise orbit determination (POD) technique. The resulting Jason-1 orbit accuracy was assessed by comparison with the precise orbit ephemeris (POE) produced by JPL, orbit overlaps and SLR residuals. These evaluations indicate that the RMS radial accuracy is in the range of 1－2 cm.     

Precise orbit determination for GRACE with zero-difference kinematic method

Thanks to the high performance of the spaceborne GPS receiver and the availability of precise IGS orbit and clock products, ze-ro-difference kinematic precise orbit determination (POD) has been turned out to be a new effective method in orbit determination for the LEO satellites. Zero-difference kinematic POD, which is based on the GPS measurements only from the spaceborne GPS receiver, does not depend on the force models and orbit design. From this point of view, kinematic POD is suitable for the Earth observation satellites at very low altitudes, such as CHAMP, GRACE and GOCE, etc. This paper first reviews the basic ze-ro-difference GPS observation model. Then a modified data quality control scheme is put forward. Finally, a block-wise least squares algorithm, which first separates the parameters into several groups and then solves the parameters by elimination and back-substitution, is discussed and proposed for the kinematic orbit determination. With the above algorithms, we developed kinematic POD software to solve the orbit suitable for one-week GRACE observations. Comparisons with the published Rapid Science Orbit (RSO) indicate that, using our approach to determine the orbit, the accuracy in the radial direction can achieve 3―4 cm for GRACE-A, and 3―5 cm for GRACE-B.     

Reverse Detection Based QoS Routing Algorithm for LEO Satellite Constellation Networks

A reverse detection based QoS routing algorithm was developed based on the dynamic topology of low earth orbit (LEO) satellite constellation networks. This distributed algorithm has very low computational complexity, so it is suitable for on-board processing. This algorithm improves the autonomous operating capability and throughput of satellite networks. Simulations show that the algorithm has better performance than the static sequent snap shots algorithm with acceptable low overhead signaling.     

低轨道卫星功率带宽资源联合分配方法

由于低轨道卫星星上功率和带宽资源有限,设计有效的资源分配方法具有重要的意义.基于此提出了一种低轨道星间功率带宽资源联合分配方法,提高了星间资源分配的公平性和网络业务承载能力.该方法应用地面站数目和星地链路存在时间刻画星间链路容量的比例,将星间资源分配问题归纳为非线性混合整数规划问题.通过引入动态可行域,定义二元变量更新操作来改进燕子群算法,用于优化模型求解.仿真得出卫星瞬时吞吐容量和瞬时网络容量变化具有周期性,并伴有随机波动,所提方法牺牲了网络容量,获取了星间资源分配的公平性.     

低轨导航星座多普勒定位模型及性能分析

相较于北斗、GPS等全球卫星导航系统（GNSS）,低轨道卫星（LEO）具有更加显著的多普勒频移效应,有助于增强GNSS定位、导航和授时（PNT）服务性能。针对当前可用的LEO导航信号少,无法满足地面用户瞬时定位的问题,研究提出了基于一个由288颗LEO卫星构成的Walker星座,选取仿真了9个全球均匀分布的地面站多普勒观测值,建立了瞬时多普勒定位数学模型,并评估了其潜在的服务性能。结果表明：在中低纬度地区,LEO可视卫星为10~ 15颗左右,多普勒定位精度因子（PDOP）达到500 ~ 600;而在中高纬度地区,LEO可视卫星数达到30颗以上,对应的PDOP值降至180左右。静态多普勒定位可实现厘米至分米级精度,动态定位可实现瞬时分米至米级精度,高纬度地区的定位性能显著优于中低纬度地区。     

基于深度图强化学习的低轨卫星网络动态路由算法

为了解决高移动性导致卫星网络路由难以计算的问题,融合图神经网络和深度强化学习,提出一种基于深度图强化学习的低轨卫星网络动态路由算法。考虑卫星网络拓扑和卫星间链路的可用带宽、传播时延等约束,构建卫星网络状态,通过图神经网络对其进行表示学习;根据此状态的图神经网络表示,深度强化学习智能体选择相应的决策动作,使卫星网络长期平均吞吐量达到最大并保证平均时延最小。仿真结果表明,所提算法在保证较小时延的同时,还能提升卫星网络吞吐量和降低丢包率。此外,图神经网络强大的泛化能力使所提算法具有更好的抗毁性能。     

Precise orbit determination for geostationary satellites with multiple tracking techniques

A new precise orbit determination (POD) strategy based on the combination of satellite laser ranging (SLR) and C-band transfer ranging for geostationary satellites (GEO) is presented.Two approaches to calibrate ranging biases of the C-band ranging system are proposed,namely the two tracking system co-location comparison and the combined POD method,with calibration accuracies estimated to be 0.5 ns and 1 ns respectively.Using data from a C-band tracking network in China,POD experiments indicate that meter-le...     

Models and methods for precise determination of ionospheric delay using GPS

The basic principles and methods for precisely determining ionospheric delays in GPS observations are introduced and discussed. Various methods and models for fitting ionospheric delays based on GPS are compared and analyzed, and applications of the methods and models to the research and engineering are summarized.     

Models and methods for precise determination of ionospheric delay using GPS

The basic principles and methods for precisely determining ionospheric delays in GPS observations are introduced and discussed. Various methods and models for fitting ionospheric delays based on GPS are compared and analyzed, and applications of the methods and models to the research and engineering are summarized.     

具有星际链路的LEO/MEO卫星网络动态路由协议

针对具有星际链路的LEO/MEO卫星网络,设计了一种具有自主运行能力的卫星网络动态路由协议(SDRP).采用时间离散化的链路状态增量更新的虚拟拓扑路由算法,降低了网络开销.提出的多点转发节点选举算法,提高了路由收敛速度和网络资源利用率.仿真结果表明,卫星网络动态路由协议的路由收敛时间远小于网络稳态保持时间,路由收敛时间是OSPF的1/10,平均协议带宽占用率也大大小于OSPF,可以保证卫星网络的信息可靠传送.     

减少移动卫星对地面站干扰的计算时间

在计算中低轨道移动卫星对固定业务地面站干扰时 ,如何缩减计算时间是个突出的问题。该文提出了加大计算步长和设置仰角阈值两种方法 ,分析了理论上减少计算时间的可能性 ,并通过典型的实例计算研究了这两种方法对计算精度和计算时间的影响。结果表明 ,取样步长往往可以取到相当大 (2 0 0～ 30 0 s左右 ) ,从而使得计算时间大大减小 ;另外 ,通过设置合理的仰角阈值 (15°左右 ) ,引起的误差是允许的 ,也能使得计算时间减少为原来的 90     

基于MIMO阵列的混合波束赋形算法

低轨(low earth orbit,LEO)卫星通信可以克服恶劣地形影响实现远距离通信,面对突发灾害能快速部署解决通信问题,但是,卫星在保持高速运动的同时采用高频段的信号,容易导致通信时产生严重的信号衰落。针对此问题,基于传统遗传算法提出一种适用于混合波束赋形架构的算法。固定模拟域对数字域进行迭代优化,然后固定数字域对模拟域进行迭代优化,通过共同的待优化矩阵进行联合求解,在固定功率的前提下不断迭代优化矩阵,采用混合波束赋形方法有效减少硬件复杂度,更加接近数字波束赋形的性能。仿真表明,在混合波束赋形架构应用上,相对于传统的正交匹配追踪(orthogonal matching pursuit,OMP)算法,所提算法性能提升了6.61%。     

适用于航天器的GPS姿态测量算法和软件设计

为发展小卫星 ,需要研制成本低、小而轻又能满足精度的姿态测量系统。论述了利用全球定位系统 ( GPS)载波相位观测值进行姿态测量的原理 ,介绍了航天器姿态测量软件 THADS的算法和软件设计。在软件设计时 ,采用了周跳和粗差判定的改进方法 ,编制了相应的模块 ,结合地面实验数据进行仿真计算 ,在 1m左右的基线上姿态均方差小于0 .4°。结果表明利用 GPS载波相位进行航天器姿态测量具有良好的应用前景     

Spectrofluorimetric determination of tetracycline using Eu3+ chelation and cetyltrimethylammonium bromide

The fluorescence of tetracycline was greatly enhanced by chelation with Eu³⁺ in Tris-HCl buffer (pH8.5). The addition of cetyltrimethylammonium bromide, a cationic surfactant, further enhanced the fluorescence of tetracycline-Eu³⁺ chelates. This spectrofluorimetric method for the determination of tetracycline yielded a linear responses in the range of 10 nmol/L–10 μmol/L. The detection limit was 5 nmol/L (or 2.22 ng/mL). The recovery of tetracycline spiked in serum at levels of 1 and 0.09 μg/mL was 97.9% and 97.8%, respectively. This method is fast, sensitive and suitable for the determination of tetracycline in biological specimens. Foundation item: Supported by the National Natural Science Foundation of China Biography: Huang Zu-yun (1963-), male, Ph D.     

4-(2-吡啶偶氮)-间苯二酚光度法测定Ga3+、In3+的研究

以4 (2 吡啶偶氮) 间苯二酚(PAR)为显色剂,用光度法测定了Ga3 、In3 两种离子.实验发现,PAR与 Ga3 在pH5.5～6.5时形成桔红色络合物,λmax=505nm,在0～5.0μg·mL-1范围内符合朗伯比尔定律,表观摩尔 吸光系数ε505Ga=1.40×104L·mol-1·cm-1,桑德尔灵敏度SGa3 =0.0050mg·cm-1.In3 与PAR在pH6.0～6.5形成 桔红色络合物,λmax=505nm,在0～4.6μg·mL-1符合朗伯比尔定律,表观摩尔吸光系数ε505In=1.37×104L·mol-1·cm-1, SIn3 =0.0084mg·cm-1.pH及显色剂PAR用量对Ga3 、In3 测定影响较大.     

低密度聚乙烯熔体挤出胀大的实验和数值模拟预测

对一种国产低密度聚乙烯(LDPE)进行了经过长毛细管的挤出胀大流动实验则量，得到了挤出胀大比和流动曲线．测定了材料的线性和非线性粘弹性，并用PSM模型进行了表征，同时数值模拟了LDPE熔体的挤出胀大流动．预测结果与实验基本吻合，但在较高剪切速率下两者间还存在一定的偏差，分析了影响偏差的原因。