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- W2979768540 abstract "The article considers the estimation algorithms used in the correction schemes of aircraft inertial navigation systems. The Kalman filter and its adaptive modifications capable of functioning in the absence of a priori information on the statistical characteristics of the input as well as measurement noise are investigated. The accuracy of the algorithms was estimated using the mathematical modeling and modeling from a seminatural experiment with a real inertial navigation system. The real navigation system is installed on a fixed base, which made it possible to isolate its errors in determining the speed and then evaluate the entire vector of the INS error state using the adaptive Kalman filter. The accuracy of the error compensation was evaluated using a special technique. The results of the mathematical and semi-natural modeling confirmed the high efficiency of the developed inertial navigation system correction algorithm." @default.
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- W2979768540 date "2019-09-01" @default.
- W2979768540 modified "2023-10-17" @default.
- W2979768540 title "Simulation of Experimental Data Based Inertial Navigation Systems Errors Estimation Algorithms" @default.
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- W2979768540 doi "https://doi.org/10.1109/rusautocon.2019.8867660" @default.
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