基于星间链路的BDS导航系统实时星历和钟差分离修正

BDS导航系统授权服务通过提供实时广域差分改正,满足高精度导航用户的导航需求。研究独立时间同步支持下的BDS卫星导航系统的广域差分修正模型与方法,比较了星历和星钟误差的一维(即ICD文件中的等效钟差)和四维差分等两种模式的修正性能,利用DOP值分析了星历改正的误差传播规律。分析表明,一维差分模式的修正精度随轨道误差增加而降低,不适用于在轨卫星故障及GEO卫星轨道机动后轨道快速恢复等情况,并且会降低广域差分系统的可用性;而仅在星地观测条件下,广域差分的三维星历和钟差分离的四维差分模式稳定性较差,区域监测网分布严重限制了星历和钟差误差的分离精度。随着BDS全球系统发展,为满足星座自主导航的需求,系统将提供星间链路观测。通过建立仿真平台,对星间链路支持下的星历和星钟误差分离方法进行研究与分析,结果得出,增加星间链路观测,可以有效地分离星历和星钟误差,将星历误差传播放大因子降低约50%;与一维差分模型相比,将监测站布站稀疏区域内的用户差分改正精度提高约60%。     

三维流体动力学并行软件包NaSt3DGP及其应用

该文介绍了解算直角坐标系下不可压缩Navier．Stokes方程的大型有限差分并行软件包NaSt3DGP。介绍了其采用的区域分解算法、差分格式及计算流程；对并行效率进行了测试，作出了处理器数目和计算效率的关系曲线；把此程序应用到旋转的行星流体动力学中，分别用自检验和互检验的方法证明了修改后程序的可靠性，并且得到了满意的非线性数值模拟结果。     

嵌入式GPS/DR车载组合导航系统EKF算法软件设计

介绍一种嵌入式GPS／DR（全球定位系统／航位推算）车载组合导航（它通过GPS与DR的优势互补,提高了车辆导航系统定位数据的可靠性）的EKF（扩展卡尔曼滤波）算法软件设计方法。采用统计学原理剔除导航数据的粗差点,用扩展卡尔曼滤波进行导航参数的实时求解,采用EKF算法的GPS／DR组合导航系统有利于导航信息的稳定性、可靠性和实时性。     

差分VLBI技术在采样返回任务中的应用

针对采样返回任务中多探测器精密短弧定轨问题,研究了甚长基线干涉测量(Very Long Baseline Interferometry,VLBI)技术在两探测器间的交替观测模式、2π模糊度解算方法和数据差分处理方法,给出了星载信标的设计原则和方案。利用日本SELENE探月卫星的两个小卫星R-star和V-star的同波束VLBI相关相位生成了交替VLBI相位观测量,对其进行了差分处理求解差分时延,然后利用差分时延和测速测距数据进行定轨计算。对差分时延的分析表明,交替VLBI差分群时延RMS值为46 mm,测量精度与同波束VLBI差分群时延相当;交替VLBI差分相时延RMS值为1.6 mm,测量精度与同波束VLBI差分相时延相当。定轨结果表明,交替VLBI在进行多探测器的短弧定轨时能达到同波束VLBI相当的精度。     

同波束VLBI差分相位抖动与角距离的关系模型

在有2个探测器的深空探测中,利用同波束VLBI技术可解算高精度的差分相时延,进而同时提高2个探测器的测定轨精度。但是,差分相时延的解算条件严格,差分相位抖动较大时直接影响解算的成功率。针对这一问题,利用SELENE两颗小卫星Rstar和Vstar的4个测站长达1年的同波束VLBI观测数据,统计得出了差分相位抖动与其对应的角距离的关系模型。该模型的建立,既有利于提高同波束VLBI差分相时延的解算成功率,又对行星中性大气和电离层掩星观测研究具有重要的参考意义。     

探月卫星同波束VLBI差分相位时延闭合计算与分析

针对同波束干涉测量中差分相位时延模型验证、解算结果周跳检测与校正问题进行分析。给出了相位闭合和差分相位时延闭合计算原理与方法,并以SELENE任务中解算的差分相位时延数据为算例进行分析,差分相位时延闭合计算结果小于几皮秒。验证了差分相位时延基于同一波前的模型,可用于对差分相位时延中周跳问题进行检测,可对数据波动情况进行监视,为数据后处理提供依据。在实际应用中,该方法可随着数据处理过程的推进同步进行,因此,十分有利于同波束干涉测量方法的实时实施,并应用于卫星导航。     

状态转移矩阵的差分算法及其应用

指出用数值积分方法计算状态转移矩阵在程序实现时存在的困难。根据精密定轨和参数解算的实际需要,提出用差分算法,即通过两条接近的轨道的差来计算状态转移矩阵差分算法的优点是程序具有良好的结构且编程简单,其不足之处是差分时可能损失精度。将差分算法与数值积分方法的结果进行比较,提出克服其不足处的方法。     

绝对差分算法误差对测大气视宁度的影响分析

对绝对差分算法检测太阳边缘的起伏测量白日视宁度的方法进行了研究,并对绝对差分的结果进行二阶拟合使之可以达到亚像素的检测精度。对可能的影响因素如噪声和像差等进行了分析和数值模拟,算法的精度优于0．1”。模拟结果表明,采用绝对差分算法可以对白日视宁度进行高精度的测量,最后用绝对差分算法对实际数据进行了处理,给出了初步结果。     

月球交会对接VLBI差分时延研究

中国探月3期任务中,月球交会对接技术是任务成功的重要保障.利用嫦娥3号(CE03)绕月飞行的VLBI (Very Long Baseline Interferometry)时延数据,模拟仿真绕月交会对接过程中,同波束VLBI观测模式下,差分群时延的变化情况.仿真结果显示,在远程导引段,轨道器和上升组合体轨道距离保持100 km,持续半小时,差分群时延很好地反映了两者的轨道信息,可以用于定轨定位;自主控制段,上升组合体靠近轨道器,在轨道距离从5 km减小到20 m过程中,上升组合体加速追赶轨道器时,差分群时延快速趋近于0,上升组合体减速远离轨道器时,差分群时延绝对值快速变大.最后,利用嫦娥3号奔月段同时发射两个DOR (Differential One-Ranging)信号的VLBI时延数据,计算差分相时延,初步展示了月球交会对接过程中同波束VLBI差分相时延的误差情况.     

GPS监测电离层活动的方法和最新进展

全球定位系统(GPS)可以快速、准确地提供电离层总电子含量(TEC)信息。简要介绍了GPS技术精确测量TEC、监测电离层的原理和方法，指出进行TEC绝对量估计时求解差分群延迟(DCB)的重要性，以及建立多层和实时电离层监测模型的必要性。分析了影响TEC估计的主要误差源，着重介绍了目前GPS监测电离层的最新成果和进展。     

Description of the trajectory functions of TOPEX/POSEIDON navigation

TOPEX/POSEIDON is a joint American/French ocean topography experiment. It was launched by an Ariane launch vehicle on August 10, 1992 to study and map ocean circulation. The primary functions of the navigation subsystem of the TOPEX/POSEIDON project are to establish and maintain a pre-designed reference orbit, and to measure, monitor, and predict the satellite ground track continuously. To fulfill these functions, trajectory analysis is required to design and generate all trajectory related products. This paper is concerned with the trajectory functions of TOPEX/POSEIDON navigation. It describes various activities of this support function.     

区域GPS网实测电离层变化和卫星硬件延迟的可靠性研究

根据高精度卫星导航定位的实际需要,介绍了利用中国GPS区域网双频相位平滑伪距实测数据,准实时监测区域网电离层电子总含量(TEC)变化和GPS卫星硬件延迟(DCB)的方法和结果.着重研究了区域网独立测定DCB的可靠性,利用中国境内的GPS站点分别构造了3个大小不同的区域网,通过实测DCB和垂直电子总含量(VTEC)与CO...     

导航战背景下的天文导航技术—天文导航技术的历史、现状及其发展趋势

综述近30年来我国内外天文导航技术及其相关理论和方法的进展，介绍世界各军事大国对天文导航的认识，并就天文导航在导航战背景下的显著优势进行论述。包括下列主要内容：（1）天文导航设备的历史和现状；（2）天文导航理论的新成果；（3）各军事大国对天文导航的态势；（4）天文导航的优势性；（5）天文导航自动化的主要关键技术，（6）天文导航自动化技术的发展趋势。     

Regularization and the computation of optimal trajectories

A completely regular form for the differential equations governing the three-dimensional motion of a continuously thrusting space vehicle is obtained by using the Kustaanheimo-Stiefel regularization. The differential equations for the thrusting rocket are transformed using the K-S transformation and an optimal trajectory problem is posed in the transformed space. The canonical equations for the optimal motion in the transformed space are regularized by a suitable change of the independent variable. The transformed equations are regular in the sense that the differential equations do not possess terms with zero divisors when the motion encounters a gravitational force center. The resulting equations possess symmetry in form and the coefficients of the dependent variables are slowly varying quantities for a low-thrust space vehicle.Presented at the Conference on Celestial Mechanics, Oberwolfach, Germany, August 17–23, 1969.     

Navigation formula to A. Busemann's variation problem of space travel

The indicatrix of the variation problem is given (1) by the perturbation differential equation for the semi-major axis and eccentricity, and (2) by a relation between the momentum and eccentric anomaly. The Hamiltonian equations of an extremal solution, therefore, reduce to a navigation equation. The remaining perturbation equations for the longitude of perihelion and the mean longitude at epoch, finally, yield the time dependence that gives the most economic fuel consumption.     

X射线脉冲星导航可用目标源研究

脉冲星具有自转非常稳定的特性,在空间自主导航中有重要的应用前景.选择和研究一组适合于脉冲星导航使用的候选目标源非常重要,决定脉冲星导航精度的主要因素有:导航目标源X射线流量强度、目标源的位置精度和旋转参数精度.对可用于导航的一些X射线源进行了讨论研究,并对最适合做导航研究的转动能驱动的X射线脉冲星进行统计分析.     

基于GPS与三轴磁强计的联合导航算法

为了修正近地轨道(小于1000 km)地磁场模型,提高导航的精度,在地磁导航系统中引入GPS作为一个新的测量设备,提出了一种基于三轴磁强计与GPS的联合导航算法．该算法取卫星的位置和速度向量作为状态向量,建立状态方程;取卫星周围的磁场强度和GPS接收的信号作为观测量,建立观测方程;并以GPS确定的轨道状态量为标准量,去估计磁场模型参数的修正量,构成冷备冗余导航算法．仿真结果表明,提出的导航算法对轨道位置的估计误差小于50 m,速度的估计误差小于0．1 m／s,导航算法的精度和收敛性都优于使用单一地磁导航的系统．     

Future Satellite Gravimetry for Geodesy

After GRACE and GOCE there will still be need and room for improvement of the knowledge (1) of the static gravity field at spatial scales between 40 km and 100 km, and (2) of the time varying gravity field at scales smaller than 500 km. This is shown based on the analysis of spectral signal power of various gravity field components and on the comparison with current knowledge and expected performance of GRACE and GOCE. Both, accuracy and resolution can be improved by future dedicated gravity satellite missions. For applications in geodesy, the spectral omission error due to the limited spatial resolution of a gravity satellite mission is a limiting factor. The recommended strategy is to extend as far as possible the spatial resolution of future missions, and to improve at the same time the modelling of the very small scale components using terrestrial gravity information and topographic models.We discuss the geodetic needs in improved gravity models in the areas of precise height systems, GNSS levelling, inertial navigation and precise orbit determination. Today global height systems with a 1 cm accuracy are required for sea level and ocean circulation studies. This can be achieved by a future satellite mission with higher spatial resolution in combination with improved local and regional gravity field modelling. A similar strategy could improve the very economic method of determination of physical heights by GNSS levelling from the decimeter to the centimeter level. In inertial vehicle navigation, in particular in sub-marine, aircraft and missile guidance, any improvement of global gravity field models would help to improve reliability and the radius of operation.     

Estimation of unmodeled forces on a lunar satellite

In previous investigations, a procedure for sequentially estimating the state of a lunar orbiting space vehicle acted upon by unmodeled terms in the lunar potential has been developed. Results obtained by processing tracking data from the Apollo 10 and 11 missions indicate that the algorithm provides more precise estimates of the vehicle state than conventional orbit determination procedures and, hence, provides an accurate input for navigation purposes. The question of the agreement of the estimates with the actual unmodeled accelerations has not been established. This investigation considers the question of the accuracy with which the algorithm can estimate the acceleration due to unmodeled lunar surface mascons. It is shown that an accurate estimate of the time history of the unmodeled acceleration can be obtained. The investigation also considers the effects of the magnitude and location of the mascons, as well as the effect of the observation accuracy.