MODELING OF NON-PLATFORM INERTIAL NAVIGATION SYSTEM AS A COMPONENT OF AIRCRAFT NAVIGATION COMPUTER STAND

Markelov Vladimir V., Shukalov	  Anatoly  V, Kostishin Maksim O. , Zharinov Igor Olegovich, Zharinov Oleg O

2017 , VOLUME 17, NUMBER 5 ( September-October )

ISSN 2226-1494 (print), ISSN 2500-0373 (online)

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Nikiforov
Vladimir O.
D.Sc., Prof.

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doi: 10.17586/2226-1494-2017-17-5-903-909

MODELING OF NON-PLATFORM INERTIAL NAVIGATION SYSTEM AS A COMPONENT OF AIRCRAFT NAVIGATION COMPUTER STAND

V. V. Markelov, A. V. Shukalov, M. O. Kostishin, I. O. Zharinov, O. O. Zharinov

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Article in Russian

For citation: Markelov V.V., Shukalov A.V., Kostishin М.О., Zharinov I.O., Zharinov O.O. Modeling of non-platform inertial navigation system as a component of aircraft navigation computer stand. Scientific and Technical Journal of Information Technologies, Mechanics and Optics, 2017, vol. 17, no. 5, pp. 903–909 (in Russian). doi: 10.17586/2226-1494-2017-17-5-903-909

Abstract

Subject of Research. The non-platform inertial navigation system mathematical model is proposed. The non-platform inertial navigation system is an aircraft flight navigation parameters detector and a part of the airborne equipment. This model as a part of the simulation stand provides the modeling of the aircraft flight navigation parameters including the inaccuracies that may occur when a real non-platform inertial navigation system is active. Method. The flight navigation parameters calculation with the use of the proposed model is based on the calculation of simulated functioning parameters of the inertial system in horizontal plane. The initial data for calculation are the current programmed values of the flight navigation parameters and the aircraft orientation parameters without paying attention to the angular velocity and acceleration. The model initial data can be programmed with the simulation stand. The model contains the mathematical apparatus modeling inaccuracies that may occur when the inertial coordinates system tries to determine the aircraft location and its ground speed. Main Results. The proposed model provides the geodesic coordinates calculation and the ground speed when the orientation inaccuracies constant components are programmed including the gyroscope drift and the inertial system accelerometer inaccuracies. The modeling inertial system technical characteristics can determine the inaccuracy values, in particular, for the systems based on the ring laser gyroscopes. The model work-out results with the use of flight test data are given and the modeling inertial system inaccuracies evaluation is presented. Practical Relevance. The modeling realization of the non-platform inertial navigation system parameters as a part of the airborne equipment stand provides the information display system functioning work-out on the ground. At the analysis of basic design requirements for equipment development the inertial system model can be used for the preliminary functioning analysis of the non-platform inertial navigation system and the evaluation of the flight navigation parameters inaccuracies.

Keywords: navigation computer, non-platform inertial navigation system, mathematical model, modeling

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