INERTIAL NAVIGATION ACCURACY AND ACCELEROMETERS WITH DAMPING

Authors

  • O. A. Ivanov National Aviation University, Kyiv
  • Y. A. Opanasiuk National Aviation University, Kyiv

DOI:

https://doi.org/10.18372/1990-5548.57.13229

Keywords:

Inertial navigation system, accelerometer, wave equation, disturbing influences Lagrange function, inertial management unit

Abstract

Nowadays an anxiously important problem is the creation of the low-cost gyro-free inertial navigation systems. That is why we focus primarily on linear accelerometer to avoid gyro using. The problem of inertial navigation accuracy with using of accelerometers in inertial measurement unit are discussed. It is shown that a strict successive analysis of accelerometer measurement procedure makes it possible to understand probable new source of errors in the value estimation of the disturbing force magnitude. If do not take into account these new possible errors any self-adjusting system of an airplane may be functionally unreliable. These errors arise primarily when temporal duration of disturbing force is less than some critical time τ, which depends on the given characteristics of an aircraft Inertial Navigation System and aircraft itself. The method of finding τ is proposed. A presence of a damping force in the proof mass motion equation is examined.

Author Biographies

O. A. Ivanov, National Aviation University, Kyiv

Aviation Computer-Integrated Complexes Department, Educational & Research Institute of Information and Diagnostic Systems

Bachelor

Y. A. Opanasiuk, National Aviation University, Kyiv

Aviation Computer-Integrated Complexes Department, Educational & Research Institute of Information and Diagnostic Systems

Senior Lecturer

References

V. M. Sineglasov and F. M. Zaharin, “Perspectives of integrated inertial-satellite systems development of aircraft of civil aviation,” 2-nd International Conference “Methods and Systems of Navigation and Motion Control”. Proceedings. Oct. 9-12, 2012, Kyiv, Ukraine.

V. Laria and A. Tunik, “Gyro-free accelerometer based SINS: Algorithms and Structures,” 2-nd International Conference “Methods and Systems of Navigation and Motion Control”. Proceedings. Oct. 9-12, 2012, Kyiv, Ukraine.

Y. Opanasiuk, “Theoretical framework to construct optimal flights safety diagnostic procedures,” 2-nd International Conference “Methods and Systems of Navigation and Motion Control”. Proceedings. Oct. 9-12, 2012, Kyiv, Ukraine.

Kenneth R. Britting. Inertial Navigation System Analysis, John Wiley&Sons, 1971

Yu. Opanasiuk. “Inertial Measurement Unit and External Influence Duration” 2018 IEEE 5th International Conference on MSNMC”, Proceedings Oct 16-18 2018, Kyiv Ukraine.

I. V. Savelyev, Physics General Course. Moscow, “Mir”, 1980.

L. D. Landau and E. M. Lifshits, Mechanics, Third Edition. Moscow, “Nauka,” 1973, (in Russian).

Downloads

How to Cite

Ivanov, O. A., & Opanasiuk, Y. A. (2018). INERTIAL NAVIGATION ACCURACY AND ACCELEROMETERS WITH DAMPING. Electronics and Control Systems, 3(57), 30–35. https://doi.org/10.18372/1990-5548.57.13229

Issue

Vol. 3 No. 57 (2018)

Section

THEORY AND METHODS OF SIGNAL PROCESSING

License

The scientific journal “Electronics and control systems” adheres to the principles of Open Access and provides free, immediate, and permanent access to all published materials without financial, technical, or legal barriers for readers.

All articles are published in Open Access under the Creative Commons Attribution 4.0 International (CC BY 4.0) license.

Copyright

Authors who publish their works in the journal “Electronics and control systems”:

  • retain the copyright to their publications;

  • grant the journal the right of first publication of the article;

  • agree to the distribution of their materials under the CC BY 4.0 license;

  • have the right to reuse, archive, and distribute their works (including in institutional and subject repositories), provided that proper reference is made to the original publication in the journal.