EVALUATING TWO NAVIGATION SYSTEMS ERROR DEVIATION ALGORITHM
The integration of an inertial navigation system and the global navigation satellite system is designed to ensure reliable, safe and stable performance of aircraft navigation systems. To achieve this, it is advisable to emphasize the following requirements - maintaining / ensuring /preserving the accuracy of the parameters of navigation systems during long-term operation; ensuring the simplicity and reliability of the algorithm for integrating the navigation system, which requires low processing performance by on-board computers of the aircraft. To meet the above requirements, a centralized Kalman filter method was used, used for integration of global navigation satellite system and inertial navigation system systems in conditions of weak communication/signals. Firstly, this integration method is quite compact in implementation, which significantly reduces the amount of calculations and simplifies the complexity of the system. Secondly, IN Snavigation parameters error is calculated using the discrete Kalman filter algorithm, is returned to the system by the feedback correction method, which eliminates the problem of reducing the accuracy of navigation parameters after prolonged operation. The results of this work are depicted by modeling the error in aircraft navigation parameters in flight after filtering. The robustness and effectiveness of the proposed algorithm has been tested.