Analysis of the Strapdown Inertial Navigation System (SINS) Error Genesis

Transport and Aerospace Engineering 2018
Pjotrs Trifonovs-Bogdanovs, Anvar Zabirov

Analysis and simulation of the Strapdown Inertial Navigation System (SINS) error genesis revealed that the East Feedback Contour has the greatest influence on the development of an error in this model, and angular velocity sensor 𝚫𝝎𝒚 is the critical element. In order to prevent the development of an error, structural correction in the East Feedback Contour, and elements that are more critical, namely in angular velocity measurement sensors is the best option.

Keywords
Feedback loops, inertial reference system (IRS), SINS error model simulation, SINS simulink analysis, strapdown inertial navigation system (SINS)
DOI
10.2478/tae-2018-0006
Hyperlink
https://content.sciendo.com/view/journals/tae/tae-overview.xml

Trifonovs-Bogdanovs, P., Zabirov, A. Analysis of the Strapdown Inertial Navigation System (SINS) Error Genesis. Transport and Aerospace Engineering, 2018, Vol. 6, No. 1, pp.44-54. ISSN 2255-968X. e-ISSN 2255-9876. Available from: doi:10.2478/tae-2018-0006

Publication language
English (en)