基于双星定位系统的近地卫星联合定轨建模及精度分析

通过对基于双星定位系统的近地卫星联合定轨测量模式的分析,建立了基于距离和观测数据的联合定轨模型,构建了一种有效的系统误差参数估计方法,设计了一种基于数值融合法的联合定轨算法.仿真计算结果表明,联合定轨方式可以较好地抑制静地卫星星历误差对近地卫星定轨精度的影响,两天观测数据下近地卫星定轨精度可以达到11.26米,验证了本文所提出的系统误差估计方法及数值融合实现算法的有效性.     

地面基准站网与星载GNSS融合的高中低轨卫星联合精密定轨

下一代导航系统拟纳入低轨卫星（LEO）作为增强和备份。研究了地面基准站网与星载GNSS融合的高中低轨卫星联合精密定轨（POD）理论与方法，基于实测国际地面站（IGS）和低轨卫星星载GNSS数据，通过建立高精度动力学模型和观测模型，根据全球测站和区域测站两种情况进行了导航星与低轨星的联合精密定轨试验。结果表明，联合定轨可同时获得导航星和低轨星厘米级的定轨精度。低轨星作为高动态天基测站，对导航星定轨精度的提升程度可达20%~90%。     

面向高轨航天器的北斗导航特性分析

利用卫星导航信号实现高轨航天器的自主定轨与导航已成为当前国内外的研究热点， 高轨星载导航接收机面临可见卫星数少、接收导航信号微弱、动态性较大等问题。针对以上问题， 分析了高轨环境下星载导航接收机获取到的信号功率、可见星数、DOP 值及多普勒频移状态。首先建立了北斗星座模型与高轨航天器动力学模型，构建星间测距链路，对高轨卫星的可见性进行了仿真分析，结果表明当星载接收机功率为-177 dBw 时，可见星数能达到 4 颗以上，能满足定轨需求；然后对高轨卫星的定轨精度进行了仿真，DOP 值的均值为 15.657 8；最后对导航卫星和高轨卫星之间的多普勒频移进行了分析，仿真的多普勒范围为±14 kHz。相关研究结果可支撑高轨航天器星载接收机的开发。     

星载GPS辅助低轨卫星运动学定轨方法综述

本文简要介绍了星载GPS低轨卫星定轨的背景、系统组成和主要定轨方法。重点论述了星载GPS低轨卫星运动学定轨的基本原理及方法,指出了各种运动学定轨方法的优点和不足。分析了各种运动学定轨解算的特点,并对星载GPS低轨卫星运动学定轨的发展方向进行了展望。     

低轨卫星信号捕获与跟踪技术综述

低轨(Low Earth Orbit, LEO)卫星互联网相较于地面网络有更大的网络覆盖范围与更强的网络稳定性,有利于实现全球立体无缝网络覆盖,是未来6G网络重要的发展趋势。低轨卫星相较于中高轨卫星具有更高的运行速度,因此,低轨卫星信号具有更大的多普勒频移和动态特性,而低轨卫星信号的高精度捕获与跟踪是低轨卫星通信的基础。随着相控阵天线在低轨卫星和卫星终端上的推广应用,多波束和跳波束技术也为信号的捕获与跟踪带来挑战。从低轨卫星信号互联网的信号特点出发,提出了信号捕获与跟踪过程中的技术挑战,重点阐述了现有捕获与跟踪方法的基本原理与适用范围,探讨了低轨卫星网络中信号捕获与跟踪技术的未来发展方向。     

星箭分离前后的联合统计定轨方法

提出了利用星箭分离前后包括对火箭和卫星测量的多测段数据进行统计优化的定轨方法.在定轨过程中,分别采用了基于单位矢量的状态转移矩阵构造方法和有限差分法来计算状态转移矩阵,对两种方法的特点进行了分析,并对分段定轨和联合定轨在两种定轨方法下的计算结果进行了比较.计算结果表明,在星箭分离速度增量与实际情况一致的情况下,联合定轨...     

基于星间测距的卫星自主定轨研究与仿真

提出了一种利用星间距离信息和扩展卡尔曼滤波算法确定卫星的位置和速度的方法。利用STK软件建立GPS星座,将1颗目标卫星与3颗参考卫星之间的距离引入一定的误差作为星间观测值,利用扩展卡尔曼滤波算法实现卫星的自主定轨。并对算法进行了改进,利用几何准确度因子GDOP值控制参考卫星的选择,消除了误差峰值。运算结果表明改进后的算法有很好的收敛性,提高了定轨准确度。     

我国GEO卫星高精度测定轨技术进展

同步轨道卫星在通信、气象、导航定位、对地观测、数据中继等领域应用广泛,对其轨道精度的要求也越来越高。结合国内外卫星系统的高精度测量体制,介绍了我国GEO卫星高精度测定轨技术的2个发展趋势:厘米级高精度多站测距技术和主动CEI测量定轨技术,给出了相应的误差分析、关键技术及解决途径,并介绍了最新试验进展。试验结果表明,给出的2种技术体制均能够实现近10 m量级的GEO卫星实时定轨精度,满足我国GEO卫星的高精度测定轨需求。     

一种单星对同步轨道卫星的仅测角定位跟踪算法

针对中低轨卫星对同步轨道卫星定位时存在的可观测时间短等限制,结合同步轨道卫星轨道的特点,利用测角信息计算出距离信息。将距离信息与测角信息一起建立新的测量方程,进而提出一种新的基于J2000.0惯性系的单颗中低轨卫星对同步轨道卫星的扩展卡尔曼仅测角被动跟踪定轨方法,并对测量方程的变量和坐标转换给出了明确定义。仿真结果表明,该算法实现了单颗中低轨卫星对同步轨道卫星的仅测角被动跟踪定轨,若已获得被测星的先验知识,该算法收敛时间优于未引入距离信息的常规算法。     

Passive Orbit Measurement of Geosynchronous Satellite Based on Four-station's Time Difference of Arrival

基于卫星通信信号的多站时差测轨是一种重要的新型无源测轨方法,分析其定轨精度对系统应用具有重要意义.介绍了四站时差测轨原理与系统组成,提出了基于四站时差测量数据的自校准统计定轨策略,采用计算机仿真了同步轨道卫星的统计定轨精度.仿真结果表明:当无系统误差时,24h观测数据统计定轨位置误差约为11m,预报1周位置误差约100 m;当存在系统误差时,可用自校准方法同步估计系统误差,系统误差估计精度约为4m,位置误差约为120 m,预报1周的位置误差约为200 m.     

'Optimal energy allocation and admission control for communications satellites

We address the issue of optimal energy allocation and admission control for communications satellites in Earth orbit. Such satellites receive requests for transmission as they orbit the Earth, but may not be able to serve them all, due to energy limitations. The objective is to choose which requests to serve so that the expected total reward is maximized. The special case of a single energy-constrained satellite is considered. Rewards and demands from users for transmission (energy) are random and known only at request time. Using a dynamic programming approach, an optimal policy is derived and is characterized in terms of thresholds. Furthermore, in the special case where demand for energy is unlimited, an optimal policy is obtained in closed form. Although motivated by satellite communications, our approach is general and can be used to solve a variety of resource allocation problems in wireless communications.     

天基监视中的双星相对运动模型研究

以天基监视为背景,依据几何学原理和矢量计算工具,主要研究了双星相对运动模型。一方面,突破力学求解方式,采用一种区别于传统轨道根数的卫星轨道生成规则,可清晰直观地描述卫星轨道;另一方面,结合光电跟踪系统,研究了双星运动过程中的相对方向变化。通过对异面太阳同步圆轨和共面地球同步圆轨双星相对运动模型的仿真计算,获得了卫星轨道、相对距离、方位角、俯仰角、方位角速率、俯仰角速率的变化结果,分析结果证明了此方法的合理性,可为天基监视中的工作区域选择、卫星轨道设计、监视系统设计和捕获跟踪瞄准控制系统设计等物理问题和关键技术提供定性和半定量参考。     

An adaptive calibration and beamforming technique for a GEO satellite data relay

High throughput data links from low Earth orbit satellites through a geostationary orbit satellite data relay have been proposed to increase the available contact times to ground stations. Accurate antenna beam pointing and tracking of moving targets are key requirements for the relay satellite. In this work, we propose an adaptive calibration and beamforming methodology on the basis of least mean squares, which is suitable for a geostationary orbit data relay. The target system consists of the combination of a high gain reflector fed by a digitally steerable patch antenna array. The proposed method is first presented by numerical cosimulation of the antenna and the calibration algorithm. The results are then validated in an outdoor experimental setup with all digital signal processing implemented in a field‐programmable gate array. We demonstrate the tracking ability and pointing performance of the digitally enhanced reflector antenna with gain fluctuations smaller than 3 dB over a field of view of at least 2,5°. The demonstrated performance shows that the digitally enhanced reflector antenna is a suitable candidate for long‐distance space communications.     

Mobile satellite communications systems: Toward global personalcommunications

The constraints imposed by the RF environment are reviewed. An overview of present and planned mobile satellite systems is given. Present systems refer to those already in operation, while planned systems refer to those that have authority to offer the services and have either a satellite in orbit or one being built to support the systems. Future directions for mobile satellite communications systems are discussed. One approach emerging is the use of large satellites, with large antennas. operating at much higher carrier frequencies. A second approach is to use low-earth orbit (LEO) satellites. in order to reduce the path loss. The LEO approach also results in much smaller propagation delays than those experienced with geostationary satellites     

对地面某区域某时段连续覆盖的卫星轨道计算

为了对地面某一区域在未来某一时段连续覆盖,需要对在轨卫星变轨,并计算变轨后的卫星轨道参数。基于在轨卫星部分轨道参数(椭圆轨道a,i,e,圆轨道a,i)和t时刻星下点的位置坐标及卫星的地面高度,计算卫星的6个轨道参数,从而得到t时刻对星下点位置为中心的区域覆盖所需要的卫星轨道参数。利用t时刻卫星在J2000.0平天球坐标系3个坐标轴的位置与速度分量计算其卫星轨道参数。用STK卫星工具箱软件6.0高精确度轨道产生器仿真,输入所得的t时刻卫星轨道参数,运行STK 6.0得到的星下点位置与事先设置的星下点相距6.63 m,完全满足卫星对地面覆盖的需要。欲对该区域在t时刻以后的一段时间连续覆盖,所需要的卫星轨道参数可按共地面轨迹计算;通过STK 6.0高精确度轨道产生器对计算得到的卫星轨道参数进行仿真,验证了计算结果的正确性。     

欧洲下一代气象卫星及其红外遥感仪器概要

总结了欧洲气象卫星组织（EUMETSAT）与欧空局（ESA）的气象卫星发展情况以及他们对下一代地球同步轨道和极轨气象卫星的规划.下一代地球同步轨道气象卫星计划为MTG系列,将以MTG-I（成像卫星）和MTG-S（探测卫星）双星运行,各自承载不同的探测仪器,计划发射6颗卫星（4颗MTG-I和2颗MTG-S）.而极轨气象卫星MetOp-SG则与美国国家海洋和大气管理局（NOAA）/美国航空航天局（NASA）的卫星系统联合.ESA当前的MetOp卫星和下一代MetOp-SG卫星在“上午”轨道上运行,NOAA/NASA的下一代JPSS卫星在“下午”轨道上运行,双方共享两个轨道卫星数据.     

GPS-BASED LEO SATELLITE POSITION AND ATTITUDE DETERMINATION AUGMENTED BY PSEUDOLITES ON EARTH

GPS-based navigation and attitude determination of LEO satellites is presently considered as an alternative to the conventional systems which utilize earth sensors and magnetometers. The onboard GPS receiver determines the orbit position of the LEO satellite by the conventional system of linearized navigation equations, requiring the simultaneous reception of ranging signals from four GPS satellites by a single antenna. For attitude determination, pairs of antennae, suitably mounted on the satellite and feeding a common receiver, form several interferometric baselines. The baselines vectors, defined in a given coordinate system, determine the attitude of the satellite. For each baseline and each GPS satellite, the difference in phase of the received signal carriers is measured. The differencing operation eliminates the receiver clock bias. Solutions for the baseline vectors can be obtained with signals received from only three GPS satellites. If the coverage of a receive antenna is restricted to less than the hemisphere it will not have four GPS satellites in view all the time. It is demonstrated that a GPS pseudolite transmitter located on earth supplements the system, which then provides a usable geometric dilution of precision (GDOP) for position determination and an improved position dilution of precision (PDOP) for attitude determination. Pseudolites can be co-located with the gateways which provide access to the public switched telephone networks (PSTNs) for the LEO communication satellites.     

Satellite-Systems Cost Estimation

Cost-Estimate Relations (CER's) are derived for launch/orbit insertion, payload/satellite(s), and the total satellite system. These CER's are expressed in terms of orbit altitude (or apogee), orbit type (circular or elliptical), and payload weight. The CER's are also presented briefly in terms of number of rings, number of satellites per ring, and satellite weight. They are applicable only to recurring (production) costs and include an 80percent "learning-curve rate." Satellite-subsystem percent weights are also discussed for single-axis and three-axis stabilized satellites, and guidance is developed for estimating total satellite weight given the required RF power.