• 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; 20050523-25; Saint Petersburg(RU) >SENSOR ORIENTATION FROM INTEGRATED MULTI-ANTENNAE GPS AND GYROS
【24h】

SENSOR ORIENTATION FROM INTEGRATED MULTI-ANTENNAE GPS AND GYROS

机译：集成多天线GPS和陀螺仪的传感器定向

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

For the application in strapdown airborne gravimetry, the problem of attitude determination is studied. For principal reasons, the attitude shall be based on geometric observations only, i.e. on GPS-multi antennae and angular rate sensors only, without using gravity field aiding as is common in e.g. menial positioning; optical sensors like in GIS applications are not employed. Further, the alignment of the angular rate sensors to the navigation frame realised by the multi antennae GPS receiver is accomplished without prior calibration of the angular rate sensors in the laboratory, i.e. the rate sensors are neither calibrated nor strictly orthogonal. For the rate sensors, vibratory or fibre optical gyros were selected because of their light weight, compact dimensions and high resolution. A general transformation matrix is derived from the combination of the data of the two sensors collected in some flight manoeuvres in order to refer the rate sensor data to the local navigation frame. The data fusion of the two attitude (rate) sensors with an integrating filter provides high sampling rate high resolution attitudes in the navigation reference frame. The two sensors complement each other in that the multi antennae GPS conceptually provides 'drift free' but low sampling rate high noise information whereas the angular rates sensors contribute high rate high resolution but drift affected data. Another problem is whether these attitudes are really absolute values and what is the stability of the reference frame realised this way. The experiments draw the attention to the multipath effects of GPS receivers aboard aircraft. In a few static tests on top a roof of a building and in a stationary aircraft, this problem is investigated. The result is that currently multi-path at aircraft may be the most severe problem and limits the absolute attitude accuracy to somewhere below 1°, where this value depends on numerous details.
机译：为了在捷联航空重力测量中的应用，研究了姿态确定的问题。出于主要原因，该姿态应仅基于几何观测，即仅基于GPS多天线和角速率传感器，而不应使用重力场辅助，例如体位定位；像GIS应用程序一样不使用光学传感器。此外，无需实验室中的角速率传感器的事先校准即可完成角速率传感器与多天线GPS接收机所实现的导航框架的对准，即，速率传感器既不被校准也不严格正交。对于速率传感器，选择振动或光纤陀螺仪是因为其重量轻，尺寸紧凑和分辨率高。为了将速率传感器数据参考到本地导航框架，从在某些飞行操纵中收集的两个传感器的数据的组合得出了一个通用的变换矩阵。两个姿态（速率）传感器与积分滤波器的数据融合在导航参考系中提供了高采样率和高分辨率姿态。这两个传感器相互补充，因为多天线GPS在概念上提供了“无漂移”但采样率低的高噪声信息，而角速率传感器则提供了高分辨率的高速率但漂移了受影响的数据。另一个问题是这些态度是否真的是绝对值，以这种方式实现的参照系的稳定性如何？实验提请注意飞机上GPS接收器的多径效应。在建筑物屋顶和固定飞机顶部的一些静态测试中，对这一问题进行了研究。结果是，目前飞机上的多路径可能是最严重的问题，并将绝对姿态精度限制在1°以下，该值取决于许多细节。

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