Research on influence induced by installation error in SINS

WANG Song; LIU Jian-ye; LAI Ji-zhou

doi:10.13873/j.1000-97872007.09.009

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Research on influence induced by installation error in SINS

更新时间：2025-09-11

- Research on influence induced by installation error in SINS
- Issue 9, Pages: 29-31+34(2007)
- 作者机构：
  
  1. 南京航空航天大学导航研究中心
  2. 南京航空航天大学导航研究中心,江苏,南京,210016
- 作者简介：
- 基金信息：
- DOI：10.13873/j.1000-97872007.09.009
  CLC： V249.322
- Published：2007
- 稿件说明：
移动端阅览
[1]王松,刘建业,赖际舟.机载安装误差对捷联惯导系统的综合影响研究[J].传感器与微系统,2007(09):29-31+34.

WANG Song, LIU Jian-ye, LAI Ji-zhou. Research on influence induced by installation error in SINS[J]. 2007, (9): 29-31+34.
[1]王松,刘建业,赖际舟.机载安装误差对捷联惯导系统的综合影响研究[J].传感器与微系统,2007(09):29-31+34. DOI： 10.13873/j.1000-97872007.09.009.

WANG Song, LIU Jian-ye, LAI Ji-zhou. Research on influence induced by installation error in SINS[J]. 2007, (9): 29-31+34. DOI： 10.13873/j.1000-97872007.09.009.

摘要

机载惯导系统的安装误差会引起加速度计输出中的附加干扰加速度

以及陀螺仪输出中的陀螺漂移

从而对惯导系统产生影响。针对捷联惯导系统（SINS）中的机载安装误差进行了深入全面的研究

推导出角安装误差和位置安装误差同时存在时系统的误差模型

并对机载安装误差给导航系统精度带来的影响进行了系统仿真。仿真结果表明:安装角误差和位置误差对于惯导系统的精度带来不可忽视的影响

将会引起惯导系统的迅速发散

必须对其加以补偿。该研究对于提高SINS的对准精度提供了理论依据

具有较好的工程应用价值。

Abstract

Installation error in inertial navigation system causes an additional interference acceleration existed in accelerater output and gyros drift in gyros output

which can lead to navigation errors.By analysing systematically from theoretical point of viewing the installation error in strapdown inertial navigation system（SINS）

the system’s error model when there are both position-installing error and angle-installing error is concluded

and the influence on SINS’s accuracy caused by installation error is simulated.The results represent the disadvantages stemming from installation error

and the errors can cause rapid accuracy distortion of SINS which must be compensated.The research can paly a positive role in improving the accuracy in the initial alignment of the gimbaled SINS

and be valuable for engineering application.

关键词

Keywords

references

激光陀螺捷联惯性导航系统中惯性器件误差补偿技术 [J]. 熊智,刘建业,林雪原,曾庆化. 上海交通大学学报 . 2003(11)

捷联惯导初始对准中杆臂效应误差的补偿 [J]. 曹洁,刘光军,高伟,孙枫. 中国惯性技术学报 . 2003(03)

弹性机翼对机载导弹子惯导系统导航精度的影响分析 [J]. 崔乃刚,林晓辉,田鸿堂,徐伯夏. 宇航学报 . 1998(04)

平台惯导系统中杆臂效应误差的研究与分析 [J]. 何秀凤,袁信. 航天控制 . 1995(02)

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