Parametric identification of the error model for the aircraft inertial navigation system

The problem of increasing the accuracy at estimating the inertial navigation systems errors by using identifying the parameters of the model is investigated. A scheme for correcting navigation systems with an estimation algorithm is presented. The accuracy of the errors estimation for the inertial navigation system by using the nonstationary adaptive Kalman filter when the average frequency of the gyroscope random drift changes is determined. A simple method for parametric identification of the change average frequency of a random drift by using a tuning coefficient is proposed. The results analysis of the estimation algorithm modeling by using the data of laboratory experiments with the serial navigation system Ts-060K is carried out. In the models of the estimation algorithm different average frequency values of the random drift change are used. Keywords aircraft; inertial navigation system; estimation algorithm; parametric identification; average frequency of random gyroscope drift; tuning factor; estimation accuracy