Аннотация:Aircraft are controlled based on information received from navigation systems. Navigation systems have a variety of errors due to design features and operating conditions. The features of all three different inertial navigation system (INS) correction schemes are studied using the mathematical modeling algorithm. The self-organization method allows one to build a predictive model of INS errors. The model is built on the interval of the corrected INS operation. On the interval of autonomous INS operation, using this model, the INS errors and correction in the system output information are forecasted. After restoration of the GPS measurement signal, the INS correction is performed again using the Kalman filter.