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Modeling navigation system performance of a satellite-observing star tracker tightly integrated with an Inertial Measurement Unit.

机译:与惯性测量单元紧密集成的卫星观测恒星跟踪器的导航系统性能建模。

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摘要

As Global Positioning System (GPS) and similar systems have been developed, less emphasis has been placed on the use of celestial navigation, or star sighting for position determination. Celestial navigation has been used previously for heading correction in aircraft by observing known stars and the local horizon. An emerging technique is to determine a position by observing satellites in addition to stars, which satellites allow for local position estimation.;This dissertation defines the navigation system using this satellite-observing method to tightly integrate a star tracker, an Inertial Measurement Unit (IMU), and a barometric altimeter using an Extended Kalman Filter (EKF). Models of each of these components are described with emphasis added to the accuracy of the star tracker measurement of a satellite. Several system configurations are simulated comparing the performance of the estimate with respect to IMU grade, star tracker measurement accuracy, satellite orbit height, and measurement time interval parameters. In addition to system component parameters, two other variables are introduced: ephemeris error correction from a remote sensor and satellite selection algorithm.;Experimental observations, using a visible band star tracker integrated with a navigation grade IMU, showed that the observer's position can be estimated with a median distance root mean square (drms) position error of test cases of 39 m when observing satellites in Medium Earth Orbit (MEO) orbit. The drms position error was less than 65 m for 90% of test cases and was less than 21 m in 10% of the cases.;Additionally, power requirements were calculated for a satellite signal operating in imaging bands, such that a Low Earth Orbit (LEO) orbiting satellite constellation could be detected during the day. This type of signal would make it possible to operate the star tracker integrated navigation system in GPS-degraded environments with similar duration and comparable accuracy of GPS.
机译:随着全球定位系统(GPS)和类似系统的开发,对天球导航或星光瞄准的位置确定的关注已减少。天体导航以前已通过观察已知的恒星和当地地平线用于飞机航向校正。一种新兴的技术是通过观测除恒星之外的卫星来确定位置,该卫星可以进行本地位置估计。本论文定义了使用这种卫星观测方法将星跟踪仪(惯性测量单元,IMU)紧密集成的导航系统。 ),以及使用扩展卡尔曼滤波器(EKF)的气压高度计。描述了这些组件中每个组件的模型,重点介绍了卫星恒星跟踪仪测量的准确性。模拟了几种系统配置,比较了有关IMU等级,星跟踪器测量精度,卫星轨道高度和测量时间间隔参数的估计性能。除了系统组件参数外,还引入了两个其他变量:来自遥感器的星历误差校正和卫星选择算法。;使用可见波段恒星跟踪仪与导航级IMU集成进行的实验观察表明,可以估计观察者的位置当观察中地球轨道(MEO)轨道上的卫星时,测试用例的平均距离均方根(drms)位置误差为39 m。在90%的测试案例中,drms位置误差小于65 m,在10%的案例中,drms位置误差小于21 m。此外,还计算了在成像频段内运行的卫星信号的功率需求,例如低地球轨道白天可以检测到(LEO)轨道卫星星座。此类信号将使在GPS退化的环境中以类似的持续时间和相当的GPS精度操作星跟踪器集成导航系统成为可能。

著录项

  • 作者

    Pierce, Scott J.;

  • 作者单位

    Air Force Institute of Technology.;

  • 授予单位 Air Force Institute of Technology.;
  • 学科 Engineering Electronics and Electrical.
  • 学位 Ph.D.
  • 年度 2015
  • 页码 222 p.
  • 总页数 222
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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