利用广播星历确定BDS卫星飞行区域

针对北斗卫星导航系统(BDS)采用异构星座,其GEO、IGSO卫星飞行区域并非全球覆盖,传统监测站覆盖性能分析方法不宜直接应用以及导航卫星在轨运行时受到多种摄动影响,其实际运行区域与设计区域有别等问题,提出采用实测数据界定BDS导航卫星飞行区域的方法,并以BDS试验评估系统国内跟踪站网及GPS/BDS测试评估系统跟踪站网为例,分析了监测网的覆盖性能。实验证明本文提出的方法可较为合理、能够较准确地描述BDS地面跟踪站网的监测覆盖性能。     

Precise GRACE baseline determination using GPS

Precision relative navigation is an essential aspect of spacecraft formation flying missions, both from an operational and a scientific point of view. When using GPS as a relative distance sensor, dual-frequency receivers are required for high accuracy at large inter-satellite separations. This allows for a correction of the relative ionospheric path delay and enables double difference integer ambiguity resolution. Although kinematic relative positioning techniques demonstrate promising results for hardware-in-the-loop simulations, they were found to lack an adequate robustness in real-world applications. To overcome this limitation, an extended Kalman Filter modeling the relative spacecraft dynamics has been developed. The filter processes single difference GPS pseudorange and carrier phase observations to estimate the relative position and velocity along with empirical accelerations and carrier phase ambiguities. In parallel, double difference carrier phase ambiguities are resolved on both frequencies using the least square ambiguity decorrelation adjustment (LAMBDA) method in order to fully exploit the inherent measurement accuracy. The combination of reduced dynamic filtering with the LAMBDA method results in smooth relative position estimates as well as fast and reliable ambiguity resolution. The proposed method has been validated with data from the gravity recovery and climate experiment (GRACE) mission. For an 11-day data arc, the resulting solution matches the GRACE K-Band Ranging System measurements with an accuracy of 1 mm, whereby 83% of the double difference ambiguities are resolved.     

基于GIS的无人飞行器路径规划

在研究无人飞行器路径规划与飞行地理环境关系的基础上，提出了基于GIS无人飞行器路径规划方法，研究了该方法的体系结构和工作流程。应用实例表明，该方法能够有效地解决无人飞行器路径规划问题。     

中国首次发现真正会飞的“恐龙”——中华神州鸟(新属新种)

记述了辽宁义县早白垩世九佛堂组的一件初鸟类(Avialae)化石,其嘴里无牙,前肢明显长于后肢,尾巴由20多节尾椎组成,叉骨呈U字形,飞行羽毛超过了身体的长度。各种特征表明,新发现的初鸟类真正具有了飞行能力,代表了恐龙向鸟类演化过程中的又一中间环节。正式将其命名为中华神州鸟(Shenzhouraptorsinensisgen.etsp.nov.)。     

基于组合卫星导航系统的编队卫星分析

针对编队飞行中星间相对定位的任务需求,分析了卫星导航系统对编队卫星的动态观测几何问题,引入了相对定位精度衰减因子(RDOP)描述,并讨论了其性质。在对编队中单颗低轨卫星进行导航卫星GDOP分析的基础上,研究了不同编队宽度下编队集合的共视卫星和共视时段,仿真了一定场景下的编队卫星RDOP,并比较了与PDOP的大小关系。接收机的截止高度角对于导航卫星GDOP影响较大;编队宽度会影响到共视卫星的选择;而与采用单个GPS系统相比,采用GPS-Galileo组合卫星导航系统对编队卫星进行相对定位,RDOP数值明显减小,从而有利于高精度的星间位置确定。     

Formation Flying for a Fresnel Lens Observatory Mission

The employment of a large area Phase Fresnel Lens (PFL) in a gamma-ray telescope offers the potential to image astrophysical phenomena with micro-arcsecond (μ^′′) angular resolution [1]. In order to assess the feasibility of this concept, two detailed studies have been conducted of formation flying missions in which a Fresnel lens capable of focussing gamma-rays and the associated detector are carried on two spacecraft separated by up to 10⁶ km. These studies were performed at the NASA Goddard Space Flight Center Integrated Mission Design Center (IMDC) which developed spacecraft, orbital dynamics, and mission profiles. The results of the studies indicated that the missions are challenging but could be accomplished with technologies available currently or in the near term. The findings of the original studies have been updated taking account of recent advances in ion thruster propulsion technology.     

卫星编队——下一代空间光学遥感发展的方向

编队飞行是多颗卫星在共同控制律下动力学状态的耦合。利用卫星编队来实现光学稀疏孔径,是下一代空间光学遥感发展的新方向。阐述了光学稀疏孔径的概念及成像原理,讨论了空间光学遥感成像的干涉模式选择问题,并分析了菲索干涉对卫星编队的要求。     

浅谈遥感三维飞行数据模型及其在自然灾害监测与评估中的作用

采用PCI遥感图像处理软件，以山东省1：25万国土基础信息数据库部分要素的矢量数据作为控制底图，利用多项式纠正法纠正TM影像，用其等高线生成DEM。在FLY模块下，分别装入纠正好的TM影像和DEM，即可生成遥感信息三维飞行数据模型。该模型真实地再现了地貌形态以及遥感影像上的山川、河流、道路和村庄。这些信息是领导正确指挥防洪、泄洪的科学依据，是自然灾害的快速监测与评估的有力技术支柱。     

关于星座小卫星的编队飞行问题

从轨道力学角度来看星座小卫星编队飞行和星星跟踪中的伴飞，遵循着如下动力学机制：(1)在各小卫星绕地球运动过程中轨道摄动变化的主要特征决定了星-星之间的空间构形，(2)当星星之间相互距离较近时，在退化的限制性三体问题(实为限制性二体问题)中，共线秤动点附近的条件周期运动亦可在一定时间内制约星-星之间的空间构形．将具体阐明这两种动力学机制的原理和相应的星星之间的相对构形，并用仿真计算来证实这两种动力学机制的适用范围，为星座小卫星编队飞行和在伴飞运动过程中进行轨控提供理论依据和具体的轨控条件．