The study of the efficiency of navigation system integration algorithms based on the extended Wiener filter

Integration of the resulting output signals of the global navigation satellite system (GNSS) and the inertial navigation system (INS) is designed to ensure reliable, safe and stable performance of the aircraft navigation system. To achieve this goal, it is necessary to meet the following requirements for the obtained navigation parameters: high accuracy, continuity of information provision during long-term operation, reliability of the integration algorithm with acceptable computational costs of the aircraft onboard electronics. This paper examines the extended Wiener method for integration of GNSS and INS navigation systems under conditions of an unstable navigation data supply. Processing of navigation information from measuring devices is the basis for ensuring flight safety and aircraft control accuracy. Navigation parameters are measured as part of an integrated modular avionics system, including global navigation satellite systems (SRNS), inertial navigation system (INS), GPS/GLONASS and radar systems. The results of modeling the error in aircraft speed and position after applying the extended Wiener filter are presented. The effectiveness of the proposed algorithm was assessed based on strict statistical criteria.

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