Method for improving the accuracy of aircraft navigation system using the Kalman filter

Authors: Hu Yuhui, Ma Deng
Published in issue: #9(38)/2019
DOI: 10.18698/2541-8009-2019-9-529
Category: Informatics, Computer Engineering and Control | Chapter: System Analysis, Control, and Information Processing, Statistics
Keywords: Kalman filter, aircraft, Gaussian white noise, inertial navigation system, GPS, error of navigation systems, forecast, error compensation
Published: 03.10.2019

This article presents algorithms of the classical Kalman filter compensating errors in navigation systems of aircraft. The use of the Kalman filter to compensate errors in measuring systems in the autonomous mode is described. The analysis of the characteristics of the output signals of the inertial navigation system (INS) and satellite navigation system (SNS). A signal processing scheme for a hybrid system is presented, an algorithm is developed for synthesizing signals from INS and SNS with a Kalman filter, which implements error compensation for both systems. The results of mathematical modeling of the errors of the INS and Kalman filter are presented, and the results of estimation are compared with theoretical values. It is proved that the accuracy of the navigation system can be improved using the Kalman filter.

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