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Aerospace Instrument-Making

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The model of the three-component integrated inertial-satellite navigation system corrected using astro-information
A.S. Devyatisil’niy, K.A. Chislov

Within framework of the inertial navigation method representations a model of the system with function of gravitational field strength determination is offered and explored. The results of numerical research characterizing numerical stability and efficiency of the gravimetry problem solution in conditions of measurements limited accuracy are presented. Key words: inertial navigation, accelerometer, gyroscope, inverse problem, astro-system, navigation satellite system, gravimetry. E-mail: devyatis@iacp.dvo.ru. Pp. 13-16.

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