Preliminary comparison of Kalman and minimax approaches to error estimation of integrated navigation system

Author

Fokin, Leonid A. ; Shiryaev, Vladimir I.

Author_Institution

South Ural State Univ. (SUSU), Chelyabinsk, Russia

fYear

2013

fDate

12-13 Sept. 2013

Firstpage

1

Lastpage

3

Abstract

In this paper, we consider possible efforts, advantages and accuracy goals of implementing minimax filter as an error vector estimator of inertial-astro-satellite navigation system. State-space error model of integrated navigation system is developed. Minimax filter formulation is given. Brief remarks on the practice and efficiency of Kalman and minimax approaches for error vector estimation for a given integrated navigation system are presented.

Keywords

Kalman filters; inertial navigation; minimax techniques; satellite navigation; space vehicles; state-space methods; Kalman approach; error vector estimator; inertial-astro-satellite navigation system; integrated navigation system; minimax approach; minimax filter; spacecraft; state-space error model; Global Positioning System; Kalman filters; Silicon compounds; State estimation; Vectors; Integrated navigation system; Kalman filter; SINS/ANS/GNSS; error model; estimation; minimax filer;

fLanguage

English

Publisher

ieee

Conference_Titel

Control and Communications (SIBCON), 2013 International Siberian Conference on

Conference_Location

Krasnoyarsk

Print_ISBN

978-1-4799-1060-1

Type

conf

DOI

10.1109/SIBCON.2013.6693599

Filename

6693599