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Journal of Projectiles, Rockets, Missiles and Guidance >

2011 , Vol. 31 >Issue 5: 16 - 18

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2011.05.035

MISSILES AND GUIDANCE TECHNOLOGY

The Design of Error Allocation Algorithm for Strapdown Attitude System

  • CHEN CI ,
  • GAO Hongyu ,
  • ZHANG Chongmeng ,
  • SHU Dongliang
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  • 1 Military Representative Office of Navy in Dalian Ship Factory, Liaoning Dalian 116005, China
    2 Tianjin Navigation Instrument Research Institute, Tianjin 300131, China

Received date: 2010-12-25

  Online published: 2025-05-30

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Abstract

With external referential velocity, the mid-precision strapdown inertial navigation system (SINS) can provide high precise attitude information for a long time when it works as a compass system. But when designing such a system, the effect of inertial component and external velocity on system attitude error should be determined. After the compass loop design had been completed, the error equations and transfer functions in the level loop and compass loop were obtained, and the attitude error caused by errors of accelerators, gyros and external velocity were analyzed, then the mathematical relationship between the steady attitude error and these source error was derived for the error allocation design of attitude system.

Key words： gyrocompass; error allocation algorithm; strapdown attitude system

Cite this article

CHEN CI , GAO Hongyu , ZHANG Chongmeng , SHU Dongliang . The Design of Error Allocation Algorithm for Strapdown Attitude System[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2011 , 31(5) : 16 -18 . DOI: 10.15892/j.cnki.djzdxb.2011.05.035

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