一种大椭圆航法导航参数计算方法研究

针对现代精确航海中的大椭圆航法导航参数计算问题,文章在分析了已有方法的基础上,通过解析几何中的空间向量分析方法对导航参数计算公式进行推导,得出了两种不同情形下大椭圆航法航程、航向角与偏航量等参数的新计算公式,然后通过算例对导出的公式精度进行验证。结果表明,公式计算精度较高,满足远距离、高精度的导航要求。同时,本文的方法具有计算公式简洁、易于实现的特点,适用于GIS环境下精确航海计算。     

卫星立体定位的仿真分析

本文从共线条件方程和前方交会的几何条件出发,推导了异轨和同轨模式下卫星立体定位的精度计算公式,仿真分析了轨道和姿态参数测量精度对卫星测绘能力的影响。实验结果表明,本文推导的精度计算公式正确合理。     

两种SAR数据目标定位的比较

和以前的定位方法相比,距离-多普勒(R—D)定位法因不需要选地面参考点进行定位,在许多遥感应用方面具有独特的优势和重要意义。本文论述了利用卫星星历数据和雷达回波数据的距离-多普勒信息对SAR图像目标定位的原理,并对相对位置定位算法的计算公式进行了推导。通过该定位方法对Radarsat和ERS图像目标进行了定位,详细说明了轨道参数、斜距参数、多普勒参数等获取方法,比较了这两种数据目标定位具体算法和精度的差异。     

卫星通信多普勒频移计算方法研究

多普勒频移是卫星通信过程中的一个不能忽视的现象。分析了目前计算圆轨道卫星星地链路多普勒频移的几种主要方法，指出了当前教材中引用较多的一个计算公式的不合理之处，并对其进行了重新推导与更正。随后给出了一种以链路距离变化率作为相对速度来计算多普勒频移的新方法。仿真结果表明，所给方法更为简便、准确。     

广播星历参数拟合算法研究

导航卫星一般采用近圆轨道,当卫星轨道偏心率或者轨道倾角接近于0时,利用GPS卫星开普勒轨道根数拟合卫星广播星历会出现一些问题。当高轨卫星轨道偏心率接近0时,广播星历拟合精度下降甚至拟合失败,为此本文提出了减少拟合参数个数、固定轨道根数M0或者延长星历参数拟合弧段长度的方法;针对GEO卫星在小倾角情况下,广播星历可能拟合失败的情况,本文提出了改变坐标系参考轨道面,在新的坐标系下拟合广播星历的方法。结果表明,改进后的拟合方法能适用于各种类型的导航卫星轨道,拟合精度在cm级或者mm级。     

POS与DEM辅助机载SAR多普勒参数估计

由于机载SAR多普勒参数受载机不稳定飞行和复杂地形影响明显,目前仍缺少有效的矢量估计法。本文对POS和DEM数据及其误差对机载多普勒参数的影响进行了分析,以距离-共面方程构建的SAR几何关系为基础,在POS和DEM数据支持下,建立了一种多普勒参数矢量估计法,并通过仿真对提出的方法进行了验证和分析。理论和仿真表明,本文方法在高山地形、不稳飞行及大斜视角等复杂条件下,亦能够为机载SAR瞬时多普勒中心提供高精度估计。     

GPS在机载雷达探测精度评估中的应用

介绍了WGS-84坐标到机载雷达坐标的转换过程和计算公式,阐述了利用GPS定位数据及其精度。在计算载机与目标的距离精度的基础上,推导了有关的计算公式,并进行了实例计算。计算结果表明：计算公式推导正确,其测距和测角精度可以作为机载雷达的精度基准,来评估机载雷达的测距、测角精度。     

星载合成孔径雷达构像方程及其应用于轨道精化的研究

星载合成孔径雷达构像方程是地理编码、立体测量、影像定位等几何处理的基础。本文首先讨论了构像方程的参数选择,在充分考虑轨道物理模型及摄动力影响的基础上,提出了一套改进的轨道模型参数。从距离方程及多普勒方程出发,详细推导了包含轨道模型参数及成像处理参数的星载SAR构像方程。作为构像方程的一个具体应用,本文研究了星载SAR影像的轨道精化问题。将构像方程线性化,对每个地面控制点列出误差方程,可以用类似于航空影像的空间后方交会的方式精确求解轨道模型参数。试验中从1∶5万地形图上量取了5个地面控制点,对一景Radarsat SAR影像进行了轨道精化。比较发现,头文件提供的轨道与精化的轨道之间有约2km的位置差异,用精化的轨道数据得到了高精度的几何校正结果。它间接地表明了轨道精化算法的正确可行。     

基于姿轨参数的高分辨率卫星遥感影像定向模型

文章在基于传统姿轨参数的高分辨率卫星遥感影像定向模型基础上,用轨道半径变化率代替轨道偏心率和近地点幅角,并通过差商内插法求解姿轨参数的偏导系数,使平差所需控制点减少为4个.对SPOT-5HRG影像的试验表明,影像定向后像方检查点中误差小于±2pixels,对地定位精度可满足1∶50 000比例尺测图要求.     

考虑地球扁率的RNAV航路规划

考虑地球扁率的影响,在地理坐标系下推算区域导航(RNAV)航路点的经纬度坐标以及各航段的初始真航线角(TC)与航线距离,为机载区域导航设备提供更为精确的航迹指引和更为快捷的直飞航线。以IAG-75椭球参数为计算依据,根据空间向量分析,导出了RNAV大椭圆圈航线的初始TC、航线距离以及基于中间插值的航路点纬度计算方法。经计算,从B215航路的阜康至大王庄,现行等角航线距离为2642km,简化大圆航线模型的航线距离为2423.8km,而考虑地球扁率影响的大椭圆航线模型的航线距离为2435.3km。     

GNSS卫星地影的一体化建模方法和星蚀参数计算

基于日地关系建立地影模型,利用数值法可以高精度计算单个卫星的地影参数,但是难以快速而全面地分析某一类卫星的地影参数变化和分布规律。本文从日、地和卫星三者的几何关系出发,提出了一种基于空间视场的卫星地影直接建模方法。首先,分别利用轨道半长轴和太阳的周年视运动确定卫星地影的大小和位置变化;其次,基于球面几何分析法推导了卫星地影参数的计算公式以及扁率摄动等对长期预报的影响改正公式。对北斗混合星座中3类卫星的地影参数分析试验表明,卫星地影模型和地影参数解析法能够快速获得中高轨近圆轨道类型的星蚀规律信息。     

天问一号拓展任务对火星低阶重力场解算的潜在贡献分析

天问一号是中国首次独立开展的行星际探测任务,实现了对火星的环绕、着陆、巡视探测。天问一号正常科学任务阶段环绕以极轨设计为主,与历史火星任务类似,对当前火星重力场模型精度改进有限,因此其拓展任务轨道选取至关重要。通过对极轨圆轨道和近赤道大偏心率轨道进行仿真模拟,分析两种典型轨道构型对现有火星重力场模型改进的可能性,基于不同误差考量仿真解算了对应6个重力场模型。借助重力场功率谱分析,发现在测量噪声为0.1 mm/s的情况下,不论采用极轨还是近赤道轨道,一个月的跟踪数据均可较好地反演出42阶次的火星重力场模型;考虑综合误差影响之后,发现两种轨道对于重力场解算精度类似,其中实施近赤道大偏心率轨道对35阶次以上约束略强。     

基于观测时间配准的升降轨InSAR数据二维形变场解算

传统差分干涉技术只能获取雷达视线方向的一维形变场,极大地限制该技术的应用。联合升降轨InSAR数据,可以解算出地表二维形变场。然而,受卫星轨道参数的限制,即使是不同的卫星,也很难做到对同一目标的同步观测,造成升降轨观测时间的不一致,进而降低二维形变解算精度。针对上述问题,文中提出一种升降轨观测时间配准方法,即以其中一轨SAR时序数据的采集时刻为参考,采用数据插值技术,对另一轨SAR时序数据获取的时间累积形变量进行内插,得到对应参考时刻点的形变量。最后,联合解算时间配准后的两个一维形变量,获取研究区域的二维形变场。为验证所提方法的有效性,文中以苏锡常地区为例,开展二维形变场的解算实验。研究结果表明,所提方法可以更加准确地反演地表二维形变场。     

基于几何配准的多模式SAR影像配准及其误差分析

星载合成孔径雷达影像干涉处理时所需方位向配准精度因成像模式的差异而有所不同,目前在精密轨道条件下以几何配准为基础辅以影像信息的配准方案因其严格的理论模型和较高的精度成为干涉处理的首选。本文以TerraSAR-X影像为例,论证了不同成像模式影像所需的配准精度和卫星轨道精度,并通过理论分析和试验证明了精密轨道条件下,利用几何配准即可满足TerraSAR-X等卫星的条带模式影像干涉处理的需要;聚束模式影像需要在几何配准的基础上利用影像相干性或谱分集进一步优化配准结果。鉴于增强谱分集偏移量估计精度最高,本文进一步利用增强谱分集对比分析了不同轨道不同DEM条件下的几何配准误差。研究结果表明:卫星轨道切向误差是几何配准的主要误差源,目前常用3种DEM几何配准差异远小于0.001个像素,均可满足Sentinel-1影像干涉配准的需要。     

利用轨道参数修正的无控制点星载SAR图像几何校正方法

使用距离多普勒模型进行SAR图像几何校正时,卫星轨道误差、系统成像参数误差和DEM高程的误差会影响几何校正精度。本文提出了一种基于轨道参数修正的星载SAR图像几何校正方法。首先利用多项式对卫星轨道进行参数化,然后使用模拟SAR图像与真实SAR图像进行匹配得到控制点来修正轨道参数,最后利用修正后的参数进行几何精校正,从而提高几何校正精度。该方法无需地面控制点,适用于不易于人工测量获取地面控制点地区的SAR图像几何校正,与基于模拟SAR图像匹配并使用多项式改正的几何校正方法相比,本文方法具有更高的精度。使用Radarsat-2图像进行试验,并使用地面实测GPS控制点验证了本方法的有效性。     

An a priori solar radiation pressure model for the QZSS Michibiki satellite

It has been noted that the satellite laser ranging (SLR) residuals of the Quasi-Zenith Satellite System (QZSS) Michibiki satellite orbits show very marked dependence on the elevation angle of the Sun above the orbital plane (i.e., the \(\beta \) angle). It is well recognized that the systematic error is caused by mismodeling of the solar radiation pressure (SRP). Although the error can be reduced by the updated ECOM SRP model, the orbit error is still very large when the satellite switches to orbit-normal (ON) orientation. In this study, an a priori SRP model was established for the QZSS Michibiki satellite to enhance the ECOM model. This model is expressed in ECOM’s D, Y, and B axes (DYB) using seven parameters for the yaw-steering (YS) mode, and additional three parameters are used to compensate the remaining modeling deficiencies, particularly the perturbations in the Y axis, based on a redefined DYB for the ON mode. With the proposed a priori model, QZSS Michibiki’s precise orbits over 21 months were determined. SLR validation indicated that the systematic \(\beta \)-angle-dependent error was reduced when the satellite was in the YS mode, and better than an 8-cm root mean square (RMS) was achieved. More importantly, the orbit quality was also improved significantly when the satellite was in the ON mode. Relative to ECOM and adjustable box-wing model, the proposed SRP model showed the best performance in the ON mode, and the RMS of the SLR residuals was better than 15 cm, which was a two times improvement over the ECOM without a priori model used, but was still two times worse than the YS mode.     

Pseudo-Stochastic Orbit Modeling Techniques for Low-Earth Orbiters

The Earth’s non-spherical mass distribution and atmospheric drag cause the strongest perturbations on very low-Earth orbiting satellites (LEOs). Models of gravitational and non-gravitational accelerations are utilized in dynamic precise orbit determination (POD) with GPS data, but it is also possible to derive LEO positions based on GPS precise point positioning without dynamical information. We use the reduced-dynamic technique for LEO POD, which combines the geometric strength of the GPS observations with the force models, and investigate the performance of different pseudo-stochastic orbit parametrizations, such as instantaneous velocity changes (pulses), piecewise constant accelerations, and continuous piecewise linear accelerations. The estimation of such empirical orbit parameters in a standard least-squares adjustment process of GPS observations, together with other relevant parameters, strives for the highest precision in the computation of LEO trajectories. We used the procedures for the CHAMP satellite and found that the orbits may be validated by means of independent SLR measurements at the level of 3.2 cm RMS. Validations with independent accelerometer data revealed correlations at the level of 95% in the along-track direction. As expected, the empirical parameters compensate to a certain extent for deficiencies in the dynamic models. We analyzed the capability of pseudo-stochastic parameters for deriving information about the mismodeled part of the force field and found evidence that the resulting orbits may be used to recover force field parameters, if the number of pseudo-stochastic parameters is large enough. Results based on simulations showed a significantly better performance of acceleration-based orbits for gravity field recovery than for pulse-based orbits, with a quality comparable to a direct estimation if unconstrained accelerations are set up every 30 s.     

Initial results of centralized autonomous orbit determination of the new-generation BDS satellites with inter-satellite link measurements

Autonomous orbit determination is the ability of navigation satellites to estimate the orbit parameters on-board using inter-satellite link (ISL) measurements. This study mainly focuses on data processing of the ISL measurements as a new measurement type and its application on the centralized autonomous orbit determination of the new-generation Beidou navigation satellite system satellites for the first time. The ISL measurements are dual one-way measurements that follow a time division multiple access (TDMA) structure. The ranging error of the ISL measurements is less than 0.25 ns. This paper proposes a derivation approach to the satellite clock offsets and the geometric distances from TDMA dual one-way measurements without a loss of accuracy. The derived clock offsets are used for time synchronization, and the derived geometry distances are used for autonomous orbit determination. The clock offsets from the ISL measurements are consistent with the L-band two-way satellite, and time–frequency transfer clock measurements and the detrended residuals vary within 0.5 ns. The centralized autonomous orbit determination is conducted in a batch mode on a ground-capable server for the feasibility study. Constant hardware delays are present in the geometric distances and become the largest source of error in the autonomous orbit determination. Therefore, the hardware delays are estimated simultaneously with the satellite orbits. To avoid uncertainties in the constellation orientation, a ground anchor station that “observes” the satellites with on-board ISL payloads is introduced into the orbit determination. The root-mean-square values of orbit determination residuals are within 10.0 cm, and the standard deviation of the estimated ISL hardware delays is within 0.2 ns. The accuracy of the autonomous orbits is evaluated by analysis of overlap comparison and the satellite laser ranging (SLR) residuals and is compared with the accuracy of the L-band orbits. The results indicate that the radial overlap differences between the autonomous orbits are less than 15.0 cm for the inclined geosynchronous orbit (IGSO) satellites and less than 10.0 cm for the MEO satellites. The SLR residuals are approximately 15.0 cm for the IGSO satellites and approximately 10.0 cm for the MEO satellites, representing an improvement over the L-band orbits.     

星蚀期北斗卫星轨道性能分析——SLR检核结果

星蚀期北斗卫星的轨道性能是北斗卫星导航系统性能分析的重要部分。了解北斗卫星导航系统星历中星蚀期轨道的精度,不仅可为系统服务性能评估提供支持,还有助于了解星蚀期精密定轨中相关模型可能存在的问题,进而为精密定轨函数模型改进提供参考。本文基于2014年1月至2015年7月的卫星激光测距资料,重点分析了星蚀期对北斗不同类型卫星轨道的影响,同时也对北斗广播星历和精密星历中整体轨道径向精度进行检核。结果表明:星蚀期内(尤其是偏航机动期间),IGSO/MEO卫星的广播星历和精密星历轨道均存在明显的精度下降;广播星历轨道径向误差达1.5~2.0m,精密星历轨道径向误差超过10.0cm。但仅从轨道径向残差序列中难以发现星蚀期对GEO卫星轨道是否有显著影响。非星蚀期间,IGSO/MEO卫星和GEO卫星的广播星历轨道径向精度分别优于0.5 m和0.9 m。IGSO/MEO卫星的精密星历轨道径向精度优于10.0cm,GEO卫星的轨道径向精度约50.0cm,且存在40.0cm左右的系统性偏差。