Dynamic error mechanism analysis of HRG

Jiayi Qi; Xue Chen; Shunqing Ren; Wang Wang

doi:10.1109/ISSCAA.2008.4776369

Dynamic error mechanism analysis of HRG

Jiayi Qi^*
, Xue Chen
, Shunqing Ren
, Wang Wang

^*Corresponding author for this work

School of Astronautics

Harbin Institute of Technology

Research output: Contribution to conference › Paper › peer-review

8 Scopus citations

Abstract

The strains of an arbitrary point on the resonator of the hemispherical resonator gyro are deduced under KirchhotT-Lyav hypothesis. The force equilibrium equations of the thin shell element are established on the basis of the calculated strains. When the gyro is subjected to three-axis angular rates and angular accelerations, the inertia force is calculated and the border motion equations of the hemispherical resonator are established, the solution of the dynamic equation is gained using Bubonov-Galerkin method. In the end, the dynamical error model of gyro is attained, the influence of angular rate and angular acceleration on the accuracy of the gyro is analyzed when the gyro bearing three-axis angular rates and angular accelerations.

Original language	English
DOIs	https://doi.org/10.1109/ISSCAA.2008.4776369
State	Published - 2008
Event	2008 2nd International Symposium on Systems and Control in Aerospace and Astronautics, ISSCAA 2008 - Shenzhen, China Duration: 10 Dec 2008 → 12 Dec 2008

Conference

Conference	2008 2nd International Symposium on Systems and Control in Aerospace and Astronautics, ISSCAA 2008
Country/Territory	China
City	Shenzhen
Period	10/12/08 → 12/12/08

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10.1109/ISSCAA.2008.4776369

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title = "Dynamic error mechanism analysis of HRG",

abstract = "The strains of an arbitrary point on the resonator of the hemispherical resonator gyro are deduced under KirchhotT-Lyav hypothesis. The force equilibrium equations of the thin shell element are established on the basis of the calculated strains. When the gyro is subjected to three-axis angular rates and angular accelerations, the inertia force is calculated and the border motion equations of the hemispherical resonator are established, the solution of the dynamic equation is gained using Bubonov-Galerkin method. In the end, the dynamical error model of gyro is attained, the influence of angular rate and angular acceleration on the accuracy of the gyro is analyzed when the gyro bearing three-axis angular rates and angular accelerations.",

author = "Jiayi Qi and Xue Chen and Shunqing Ren and Wang Wang",

year = "2008",

doi = "10.1109/ISSCAA.2008.4776369",

language = "英语",

note = "2008 2nd International Symposium on Systems and Control in Aerospace and Astronautics, ISSCAA 2008 ; Conference date: 10-12-2008 Through 12-12-2008",

}

TY - CONF

T1 - Dynamic error mechanism analysis of HRG

AU - Qi, Jiayi

AU - Chen, Xue

AU - Ren, Shunqing

AU - Wang, Wang

PY - 2008

Y1 - 2008

N2 - The strains of an arbitrary point on the resonator of the hemispherical resonator gyro are deduced under KirchhotT-Lyav hypothesis. The force equilibrium equations of the thin shell element are established on the basis of the calculated strains. When the gyro is subjected to three-axis angular rates and angular accelerations, the inertia force is calculated and the border motion equations of the hemispherical resonator are established, the solution of the dynamic equation is gained using Bubonov-Galerkin method. In the end, the dynamical error model of gyro is attained, the influence of angular rate and angular acceleration on the accuracy of the gyro is analyzed when the gyro bearing three-axis angular rates and angular accelerations.

AB - The strains of an arbitrary point on the resonator of the hemispherical resonator gyro are deduced under KirchhotT-Lyav hypothesis. The force equilibrium equations of the thin shell element are established on the basis of the calculated strains. When the gyro is subjected to three-axis angular rates and angular accelerations, the inertia force is calculated and the border motion equations of the hemispherical resonator are established, the solution of the dynamic equation is gained using Bubonov-Galerkin method. In the end, the dynamical error model of gyro is attained, the influence of angular rate and angular acceleration on the accuracy of the gyro is analyzed when the gyro bearing three-axis angular rates and angular accelerations.

UR - https://www.scopus.com/pages/publications/66449090059

U2 - 10.1109/ISSCAA.2008.4776369

DO - 10.1109/ISSCAA.2008.4776369

M3 - 论文

AN - SCOPUS:66449090059

T2 - 2008 2nd International Symposium on Systems and Control in Aerospace and Astronautics, ISSCAA 2008

Y2 - 10 December 2008 through 12 December 2008

ER -

Dynamic error mechanism analysis of HRG

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