ERRORS ESTIMATION OF EXTERNAL DISTURBANCE INFLUENCES

Authors

  • Y. A. Opanasiuk National Aviation University, Kyiv
  • B. I. Dmytrenko National Aviation University, Kyiv
  • O. Y. Krasnousova National Aviation University, Kyiv

DOI:

https://doi.org/10.18372/1990-5548.56.12946

Keywords:

Inertial navigation system, aircraft, accelerometer, wave equation, disturbing influences, Lagrange function

Abstract

The main specific points of existing air navigation schemes with relation to external disturbing influences are discussed. Some new approach to analyze in the view of admissible temporal and spatial frames basic principle on which the simplest accelerometer may be constructed is proposed. 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 don’t take into account these new possible errors any self-adjusting system of an airplane may be functionally damaged or at least functionally unreliable. These errors arise only 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 discussed.

Author Biographies

Y. A. Opanasiuk, National Aviation University, Kyiv

Education&Scientific Institute of Information-Diagnostics Systems

Senior Lecturer

B. I. Dmytrenko, National Aviation University, Kyiv

Education&Scientific Institute of Information-Diagnostics Systems

Assistant

O. Y. Krasnousova, National Aviation University, Kyiv

Education&Scientific Institute of Information-Diagnostics Systems

Candidate of Science (Engineering)

References

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Issue

Vol. 2 No. 56 (2018)

Section

MATHEMATICAL MODELING OF PROCESSES AND SYSTEMS

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