航天器测定轨技术发展综述

归纳总结了现有航天器测定轨技术的发展历程及研究现状,分析讨论了地基、天基、天文自主等现有测定轨技术的特点及优缺点,揭示了目前仍未解决的一些测定轨难题。最后,提出一种可行的基于导航星间链路的测定轨新技术,并对航天器测定轨技术发展方向给出一些建议和展望。     

低轨导航增强GNSS发展综述

低轨星座具有地面接收信号强度高、几何图形变化快的优势,能够与中高轨GNSS星座形成互补,对增强GNSS的精度、完好性、连续性和可用性具有显著优势,已成为当前卫星导航领域的关注热点。本文首先简要介绍了现有的GNSS增强系统;总结了国内外低轨导航增强星座发展现状;针对低轨导航增强,对比分析了高中低轨导航星座的优缺点;重点讨论了低轨导航增强在联合定轨、快速精密定位、空间天气监测和室内定位等方面带来的机遇;分析指出了低轨导航增强的空间段、地面段和用户段所面临的挑战。     

利用GNSS星间链路对中高轨航天器测定轨的可行性研究

目的 目前中高轨航天器精密轨道确定普遍采用地面跟踪测量体制,面临跟踪弧段不够、跟踪精度不高、无载体自主定位能力的问题。GNSS星间链路网络的建立为中高轨航天器定轨提供了新思路。介绍了基于GNSS星间链路的中高轨航天器定轨新方法,设计仿真模型分析了其可见性、定位精度、链路预算,并进行了自主定轨模拟计算。结果表明:以 GNSS星间链路实现中高轨航天器测定轨,可见星数目多、定位精度好、链路余量高,对中高轨航天器在径向的定轨精度可以达到6m 以内,切向和法向在2m 以内。本文测定轨方案可行,为GNSS在新领域的应用提供了思路。     

低轨卫星星载GNSS精密定轨的精度检核方法

基于星载GNSS的低轨卫星精密定轨是目前大地测量领域的研究热点,也是解决我国对地观测卫星精密轨道确定最有效的手段。讨论了目前低轨卫星星载GNSS精密定轨的精度评价方法,并通过对GRACE卫星的实测和仿真数据的处理和分析,讨论了这些方法在不同观测条件下的有效性与局限性。     

高轨卫星天基定轨原理演示系统的设计与实现

以高轨卫星天基定轨原理作为理论基础,设计了一种在MATLAB仿真软件环境下运行的高轨卫星天基定轨原理演示系统。该系统实现了高轨及低轨用户星轨道仿真、全球导航卫星系统（GPS、GLONASS、Galileo和Compass）星座卫星仿真、高轨卫星及地面用户星对全球导航卫星系统的可见性仿真和高轨卫星天基定轨仿真。仿真结果表明：该系统具有效能高、清晰直观等优点,也具有较强的理论和现实意义。     

多GNSS系统精密定轨ISB/IFB估计及特性分析

多全球导航卫星系统（Global Navigation Satellite System,GNSS）系统联合精密定轨需要考虑系统间及频率间偏差的影响。推导了多GNSS定轨系统间偏差（inter system bias,ISB）/频率间偏差（inter frequency bias,IFB）解算模型,以GPS系统硬件延迟为基准,给出了一种消除ISB/IFB秩亏的约束方法。试验数据结果表明,各系统ISB/IFB均表现出良好的稳定性及同一系统各卫星时间序列的一致性,BDS ISB的标准差为0.36 ns,Galileo ISB的标准差为0.18 ns,GLONASS IFB的标准差为0.51 ns;在接收机类型相同的情况下,不同跟踪站的ISB比较接近,但仍可达到ns级差异;GLONASS IFB在同一跟踪站相同频道号的卫星及不同跟踪站相同频道号卫星均表现出了良好的一致性。     

多GNSS融合的北斗卫星精密定轨

提供高精度的精密轨道产品对北斗系统的推广应用具有重要意义。给出了一种基于模糊度固定的北斗卫星多系统融合非差精密定轨方法,重点推导论述了模糊度固定的实现方法,并结合实测数据,对其精密定轨效果进行了分析,初步分析结果表明：利用本文方法,北斗GEO、IGSO、MEO卫星三维定轨精度分别达到1.263m、0.214m、0.134m,三类卫星径向定轨精度平均优于10cm,IGSO和MEO已经基本优于5cm;模糊度固定以后,北斗卫星三维定轨精度平均提高了21.8%,轨道切向精度改善最为明显,其中又以GEO卫星改进最大。     

BD卫星星间链路定轨结果及分析

我国新一代北斗导航系统试验卫星搭载了高精度星间链路载荷并已经得到了实测数据。本文给出了星间链路数据预处理方法,并介绍了星间链路数据独立定轨和星间Ka测量与L波段数据联合定轨的方法和初步结果。利用3颗试验卫星和1个地面Ka站在轨试验,结果表明:独立采用星间链路定轨,其结果 R方向误差小于0.5m;星间链路数据与L波段数据联合定轨,其对L波段定轨结果有显著改善,轨道R方向误差小于0.3m;星间测量设备时延标校精度优于0.1m。     

北斗卫星发射场系统GNSS控制网的优化设计

北斗导航卫星发射场系统GNSS控制网是为北斗卫星发射提供高精度的位置基准、射向基准及轨道测控基准,本文针对发射场系统GNSS控制网建立技术特点,以控制网观测的效率性、可靠性、经济性、精度性为优化设计指标,分别从控制基准优化选取、网形结构设计以及优化精度估算等方面对实施方案进行了优化设计,并通过实际作业验证该优化设计方法的科学性和可操作性。      

Recursive algorithm for fast GNSS orbit fitting

Gaussian elimination is an efficient and numerically stable algorithm for estimating parameters and their precision. However, before estimating the parameters, it is often prudent to perform statistical tests to achieve the best fitting model. We use Gaussian elimination to select the best fitting model among candidate models. A succinct relationship between the weighted sum of squared residuals and the previous one is revealed by a volume formula. For quick parameter estimation and determination of weighted sum of squared residuals, a recursive elimination algorithm is proposed in the context of Gaussian elimination. In order to improve the model selection efficiency, the parameter estimation and the determination of the weighted sum of squared residuals are carried out in parallel using the proposed recursive elimination algorithm in which the improvement at each recursive stage is judged by the Bayesian information criterion. Ultimately, the computational complexity and numerical stability of the recursive elimination proposed are briefly discussed, and a GNSS orbit interpolation example is used to verify the results. It shows that the proposed recursive elimination algorithm inherits the numerical stability of the Gaussian elimination, and this algorithm can be used to examine the gain from the newly introduced parameter, dynamically assess the fitting model, and fix the optimal model efficiently. The optimal fitting model with the lowest information is very close to the real situation verified by checkpoints.     

顾及卫星非圆轨道改正的GNSS精密测速方法

详细推导了卫星非圆轨道改正的计算公式,给出高精度测速顾及该项误差的处理策略．采用全球均匀分布的12个国际GNSS服务（IGS）测站的多普勒和载波相位观测数据,仿动态评估了该项误差对测速精度的影响．结果表明:基于历元间载波相位差分的测速方法,改正后东、北、天顶方向分别提高8％、9％和10％,三维测速精度从9.9 mm／s改正到8.9 mm／s;基于原始多普勒的测速方法,东、北方向与载波相位差分方法的改正数值基本一致,天顶方向约是载波相位差分方法的改正数值的一半．      

(Near-)real-time orbit determination for GNSS radio occultation processing

The processing of GPS radio occultation measurements for use in numerical weather predictions requires a precise orbit determination (POD) of the host satellite in near-real-time. Making use of data from the GRAS instrument on Metop-A, the performance of different GPS ephemeris products and processing concepts for near-real-time and real-time POD is compared. While previous analyses have focused on the achievable along-track velocity accuracy, this study contributes a systematic comparison of the resulting estimated bending angles. This enables a more rigorous trade-off of different orbit determination methodologies in relation to the end-user needs for atmospheric science products. It is demonstrated that near-real-time GPS orbit and clock products have reached a sufficient quality to determine the Metop-A along-track velocity with an accuracy of better than 0.05 mm/s that was formerly only accessible in post-processing. The resulting bending angles are shown to exhibit standard deviation and bias differences of less than 0.3 % compared with post-processed products up to altitudes of at least 40 km, which is notably better than 1 % accuracy typically assumed for numerical weather predictions in this height regime. Complementary to the analysis of ground-based processing schemes, the potential of autonomous on-board orbit determination is investigated for the first time. Using actual GRAS flight data, it is shown that a 0.5 m 3D rms position accuracy and a 0.2 mm/s along-track velocity accuracy can in fact be obtained in real-time with the currently available GPS broadcast ephemeris quality. Bending angles derived from the simulated real-time processing exhibit a minor performance degradation above tangent point heights of 40 km but negligible differences with respect to ground-based products below this altitude. Onboard orbit determination and, if desired, bending angle computation, can thus enable a further simplification of the ground segment in future radio occultation missions and contribute to reduced product latencies for radio occultation data assimilation in numerical weather predictions.     

Precise orbit and baseline determination for maneuvering low earth orbiters

GPS Solutions - Orbital maneuvers are usually performed as needed for low earth orbiters to maintain a predefined trajectory or formation-flying configuration. To avoid unexpected discontinuities...     

Enhanced orbit determination for BeiDou satellites with FengYun-3C onboard GNSS data

GPS Solutions - A key limitation for precise orbit determination of BeiDou satellites, particularly for satellites in geostationary orbit (GEO), is the relative weak geometry of ground stations....     

GNSS satellite transmit power and its impact on orbit determination

Antenna thrust is a small acceleration acting on Global Navigation Satellite System satellites caused by the transmission of radio navigation signals. Knowledge about the transmit power and the mass of the satellites is required for the computation of this effect. The actual transmit power can be obtained from measurements with a high-gain antenna and knowledge about the properties of the transmit and receive antennas as well as losses along the propagation path. Transmit power measurements for different types of GPS, GLONASS, Galileo, and BeiDou-2 satellites were taken with a 30-m dish antenna of the German Aerospace Center (DLR) located at its ground station in Weilheim. For GPS, total L-band transmit power levels of 50–240 W were obtained, 20–135 W for GLONASS, 95–265 W for Galileo, and 130–185 W for BeiDou-2. The transmit power differs usually only slightly for individual spacecraft within one satellite block. An exception are the GLONASS-M satellites where six subgroups with different transmit power levels could be identified. Considering the antenna thrust in precise orbit determination of GNSS satellites decreases the orbital radius by 1–27 mm depending on the transmit power, the satellite mass, and the orbital period.     

新太阳光压模型在GNSS定轨中的应用

太阳光压摄动是影响卫星定轨中重要的误差源,在GNSS导航卫星精密定轨过程中使用最为广泛的光压模型为ECOM模型。为了探究几种ECOM模型及其适用性,该文以超快速星历为起算轨道,分析对比经典ECOM-1模型与最新13参数ECOMC模型对GPS/BDS卫星轨道的影响。结果显示:相较于ECOM-1模型,ECOMC模型在GPS定轨中精度有所提升,特别体现在径向精度提升,单天与三天弧段在径向的解算精度分别提升了12.73%和24.74%;在BDS定轨中,采用ECOMC模型,部分GEO卫星在径向方向单天精度有12.38%的提升,而对于IGSO与MEO卫星二者精度差异不大;分析可得,由于星体结构不对称引起卫星在沿太阳-卫星方向作用的偶数阶短周期谐波扰动,引入卫星-太阳方向偶数阶项的参数估计可提升卫星径向精度。     

基于接收机位置信息的GNSS干扰源定位技术

全球卫星导航系统（GNSS）目前得到了十分广泛的应用,但是GNSS信号到达地面的功率很低,同时民用信号的格式是公开的,因此极易受到各种无意和人为故意的干扰,会对GNSS定位和授时的精度造成影响．查找和消除干扰源十分重要,目前通用的干扰源查找手段是采用测向设备实现干扰源的交叉定位,但在不知道GNSS干扰源的大致位置时,采用测向设备查找干扰源将耗费很长的时间．如果能够通过提取一些通用接收机的输出量实现干扰源的粗定位,就可以为测向定位提供初始参考位置和大概的查找范围．本文利用几乎所有的通用接收机都能输出的位置信息实现干扰源的粗定位,随着GNSS接收机逼近干扰源,会造成接收机位置信息的丢失,随着GNSS接收机远离干扰源,接收机又会重新获取位置信息,本文利用一定区域内众多受干扰的接收机的位置信息丢失点和位置信息重捕获点来实现干扰源的粗定位．通过仿真验证,分析了该技术的定位误差,仿真结果表明,该方法能够实现GNSS干扰源的粗定位,为进一步准确查找干扰源提供位置参考．      

高精度GNSS实时滑坡变形监测技术及环境建模分析研究

滑坡变形监测不仅是科学问题,也是实践问题。对地质滑坡灾害进行高精度变形监测是防灾减灾至关重要的命题。GNSS作为滑坡监测预警的重要手段之一,不仅具有连续高精度、全天候监测能力,而且是目前唯一可以直接获取滑坡地表三维矢量变形的监测手段。然而,滑坡灾害往往多发于山地丘陵等复杂环境下,加上地震、降雨等因素的诱发作用,极易影响GNSS技术的实时预处理质量和监测定位精度;此外,高价位的GNSS监测终端开销也使得大规模、高密度滑坡监测难以大规模推广应用。针对上述滑坡复杂环境影响和设备成本问题,本研究分别从高精度GNSS实时数据预处理算法、空间地形环境建模和低成本云平台监测系统3个方面进行了探讨。