Abstract
The problem of increasing the accuracy of the platform inertial navigation system of an aircraft in the absence of high-precision additional information sensors, such as GPS, is investigated. It is proposed to install angular acceleration sensors on the gyro-stabilized platform of the inertial navigation system. Using of signals from the angular acceleration sensors made it possible to generate correction signals for the inertial navigation system. Correction algorithms are developed in the structure of the inertial navigation system and in its output signal. The effectiveness of the developed algorithms has been demonstrated using semi-natural simulation with the Ts060K inertial navigation system.
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