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Journal of Projectiles, Rockets, Missiles and Guidance >

2015 , Vol. 35 >Issue 5: 5 - 8,12

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2015.05.002

MISSILES AND GUIDANCE TECHNOLOGY

Analysis of Non-synchronous Error of Gyros' Effect on Attitude Update

  • WENG Jun ,
  • QIN Yongyuan ,
  • ZHANG Qiang ,
  • LIU Zhenbo
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  • School of Automaticon, Northwestern Polytechnical University, Xi'an 710129, China

Received date: 2014-10-29

  Online published: 2025-05-28

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Abstract

Because of time-delay of sampling circuit and frequency response of gyros, output of three gyros in inertial measurement unit is asynchronous. On the basis of attitude computation equations, the effect of gyros' asynchronization on attitude calculation was analyzed and deduced firstly when phase angles of sine swaying along the vehicle's two axes were different. It is indicated that when phase angles are orthotropic and same, the effect reaches minimum and maximum respectively. The impact characteristics of gyros' asynchronous behavior was analyzed under vibration environment through 0~100 Hz, and the paper offers some proposals related to the design of inertial measurement unit.

Key words： attitude computation; asynchronization; coning motion; frequency response

Cite this article

WENG Jun , QIN Yongyuan , ZHANG Qiang , LIU Zhenbo . Analysis of Non-synchronous Error of Gyros' Effect on Attitude Update[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2015 , 35(5) : 5 -8,12 . DOI: 10.15892/j.cnki.djzdxb.2015.05.002

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