Engineering Physics Annotation << Back INERTIAL NAVIGATION SYSTEM WITH HIGH-ACCURACY ALGORITHMIC CORRECTION G.I. DHZANDZHGAVA, A.V. BABICHENKO, K.A. NEUSYPIN, A.V. PROLETARSKY, M.S. SELEZNEVA The inertial navigation system of the middle class of accuracy of the family TS060 is investigated. Increasing of the system accuracy is usually achieved by algorithmic correction using the estimation algorithm , for example, the Kalman fi lter. The model and parameters of the evaluated process are, as a rule, reliably unknown. Features of estimating the state variables of uncertain systems are considered. When evaluating linear uncertain systems, a virtual model is used in the Kalman filter. An adaptive non-linear Kalman fi lter with a self-organizing model is used to estimate nonlinear vague systems. An ensemble of selection criteria for the self-organization algorithm has been created, which makes it possible to build models with the desired characteristics. The problem of estimating errors in the navigation system of an aircraft is considered. Modeling was carried out according to the data of the laboratory experiment with the navigation system C060K. Key words: inertial navigation system, correction, Kalman filter, indefinite system, virtual model, self-organization, selection criteria, navigation systems errors, aircraft. DOI: 10.25791/infizik.05.2018.016 Contacts: E-mail: neysipin@mail.ru, E-mail: m.s.selezneva@mail.ru, E-mail: rpkb@rpkb.ru Pp. 086-093.