• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文会议>Saint Petersburg International Conference on Integrated Navigation Systems; 20040524-26; Saint Petersburg(RU) >OUTCOMES ANALYSIS FOR THE FIRST FLIGHT TEST OF THE INTEGRATED INERTIAL-SATELLITE SYSTEM OF NAVIGATION, ATTITUDE AND TRAJECTORY MONITORING OF THE LAUNCHER AND THE UPPER STAGE AT SPACECRAFT 'AMOS 2' AT GEOSTATIONARY ASCENT
【24h】

OUTCOMES ANALYSIS FOR THE FIRST FLIGHT TEST OF THE INTEGRATED INERTIAL-SATELLITE SYSTEM OF NAVIGATION, ATTITUDE AND TRAJECTORY MONITORING OF THE LAUNCHER AND THE UPPER STAGE AT SPACECRAFT 'AMOS 2' AT GEOSTATIONARY ASCENT

机译：卫星升空，航天器“ AMOS 2”升空的导航，姿态和轨迹监测综合惯性-卫星综合系统首次飞行试验的结果分析

获取原文
获取原文并翻译 | 示例
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

The description of instrument structure, principles of construction and function chart of the integrated inertial-satellite system of navigation, attitude and upper stage (US) "Fregat" flight monitoring is given. The analysis of functioning and accuracy of this system will be carried out at the first natural test December, 28, 2003 at ejection Spacecraft (SC) "Amos 2" into a geostationary orbit. The data are submitted: on change during flight of launcher "Soyuz", on active and passive US stages of number of vised navigating devices of the GLONASS/GPS; on stability of work of the equipment of satellite navigation and efficiency of the measures realized in integrated structure on its maintenance. The analysis of accuracy of the integrated system from start is given up to achievement of limiting height of functioning GLONASS/GPS receiver with revealing influence of various factors. The effect from joint processing is shown during flight of measurements GLONASS/GPS receiver and menial system. The results confirming an opportunity of periodic identification on a trajectory of ejection of mistakes of attitude of inertial system are submitted.
机译：给出了组合的惯性卫星导航系统的仪器结构，构造原理和功能图，姿态和上级（美国）“ Fregat”飞行监测的描述。该系统的功能和准确性的分析将在2003年12月28日进行的首次自然试验中，将航天器（SC）“ Amos 2”射入对地静止轨道。提交数据：有关“ Soyuz”发射器飞行过程中的变化，美国GLONASS / GPS导航设备的主动和被动阶段的数量；卫星导航设备工作的稳定性和在集成结构上对其维护实现的措施的效率。从一开始就对集成系统的精度进行了分析，直到达到了发挥功能的GLONASS / GPS接收器的极限高度，并揭示了各种因素的影响。在测量GLONASS / GPS接收器和附属系统的飞行过程中，显示​​了联合处理的效果。提出的结果证实了周期性识别在惯性系统姿态错误喷射轨迹上的机会。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号