Complementary Filter in Inertial-Doppler System of Navigation

Authors

  • Мykola Filyashkin National Aviation University, Kyiv, Ukraine
  • Yuriy Kemenyash National Aviation University, Kyiv, Ukraine

DOI:

https://doi.org/10.18372/1990-5548.80.18692

Keywords:

inertial navigation system, Doppler speed meter, Kalman filter, mutual compensation and filtering, complementary filter, frequency characteristics, spectral characteristics, filter’s time constant

Abstract

The article is devoted to filtering algorithms that are used to process flight speed data from an inertial navigation system and from a Doppler speed and angle demolition meter. It is shown that the compensation scheme and the filtering scheme, the more common name of which is the complementary filter scheme, are the most common for processing flight and navigational information in inertial-Doppler navigation systems. The paper proves the equivalence of the compensation scheme and the complementary filter scheme, and also substantiates that these schemes, unlike Kalman filtering, are simple to implement, and for design, they require the selection and setting of only one parameter - the filter time constant.
A technique for choosing the optimal value of the filter time constant is proposed, which ensures the
maximum accuracy of the estimated parameter, namely: the aircraft's cruising speed. The methodology is based on the analysis of error spectra of integrated systems: the inertial system - with a low-frequency
error spectrum, and the Doppler system with a high-frequency spectrum. Studies of synthesized filtering schemes have been conducted.

Author Biographies

Мykola Filyashkin , National Aviation University, Kyiv, Ukraine

The article is devoted to filtering algorithms that are used to process flight speed data from an inertial navigation system and from a Doppler speed and angle demolition meter. It is shown that the compensation scheme and the filtering scheme, the more common name of which is the complementary filter scheme, are the most common for processing flight and navigational information in inertial-Doppler navigation systems. The paper proves the equivalence of the compensation scheme and the complementary filter scheme, and also substantiates that these schemes, unlike Kalman filtering, are simple to implement, and for design, they require the selection and setting of only one parameter - the filter time constant.
A technique for choosing the optimal value of the filter time constant is proposed, which ensures the
maximum accuracy of the estimated parameter, namely: the aircraft's cruising speed. The methodology is based on the analysis of error spectra of integrated systems: the inertial system - with a low-frequency
error spectrum, and the Doppler system with a high-frequency spectrum. Studies of synthesized filtering schemes have been conducted.

Yuriy Kemenyash, National Aviation University, Kyiv, Ukraine

Senior Teacher

Aviation Computer-Integrated Complexes Department

References

V. O. Rogozhin, A. V. Skrypz, M. K. Filyashkin, and M. P. Mukhina, Stand-alone navigation systems for a concrete type of aircraft and their maintenance, NAU, Kyiv, 2015, 308 p.

F. M. Zakharin, V. M. Sineglazov, and M. K. Filyashkin, Algorithmic support for inertial-satellite navigation systems, NAU, Kyiv, 2011, 320 p.

M. K. Filyashkin and M. P. Mukhina, “Gyro-accelerometric method of determination of angular orientation parameters,” Systems of control, navigation and communications, no. 2(30), 2014, pp. 56–62.

M. K. Filyashkin, T. I. Maryasova, “Algorithms of suboptimal filtration in the schemes of integration of inertial-satellite systems by the method of compensation,” Electronics and Control Systems, no. 2(28), 2011. pp. 100–106. https://doi.org/10.18372/1990-5548.28.628

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Published

2024-06-25

Issue

Vol. 2 No. 80 (2024)

Section

AVIATION TRANSPORT

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