Journal of Siberian Federal University. Mathematics & Physics / Coordinate and Time-frequency Support of a Spacecraft Flight by Means of Autonomic Navigation Using Sigma-point Kalman Filter Algorithm

Full text (.pdf)
Issue
Journal of Siberian Federal University. Mathematics & Physics. 2015 8 (4)
Authors
Filimonov, Vladimir A.; Shavrin, Vyacheslav V.; Tislenkoz, Vladimir I.; Kravets, Aleksey P.; Lebedev, Vitaliy Yu.; Shkolniy, Vadim N.
Contact information
Filimonov, Vladimir A.:Research Institute of Radiotechnic Systems Tomsk State University of Control Sytems and Radioelectronics Lenina, 40, Tomsk, 634050 Russia; ; Shavrin, Vyacheslav V.:Research Institute of Radiotechnic Systems Tomsk State University of Control Sytems and Radioelectronics Lenina, 40, Tomsk, 634050 Russia;; Tislenkoz, Vladimir I.:Research Institute of Radiotechnic Systems Tomsk State University of Control Sytems and Radioelectronics Lenina, 40, Tomsk, 634050 Russia;; Kravets, Aleksey P.:Research Institute of Radiotechnic Systems Tomsk State University of Control Sytems and Radioelectronics Lenina, 40, Tomsk, 634050 Russia; Lebedev, Vitaliy Yu.:Research Institute of Radiotechnic Systems Tomsk State University of Control Sytems and Radioelectronics Lenina, 40, Tomsk, 634050 Russia; Shkolniy, Vadim N.:Research Institute of Radiotechnic Systems Tomsk State University of Control Sytems and Radioelectronics Lenina, 40, Tomsk, 634050 Russia
Keywords
autonomic navigation system; spacecraft; coordinate estimation; on board time scale bias; sigma-point Kalman filter; statistic simulation
Abstract

There are investigated errors of a spacecraft current coordinate and velocity estimates, time-frequency scale bias of the board receiver reference oscillator. The receiver is a component of the autonomic nav- igation system using signals of global navigation systems GLONASS or GPS. Estimates are formed by the navigation calculator on the bases of pseudo range and pseudo velocity measurements taken in the regime of navigation signals delay and Doppler frequencies tracking under the condition of the receiver noise. The calculator utilizes sigma-point Kalman filter. Analysis of estimations accuracy is done by the Monte-Carlo method while spacecraft moves along a high elliptic orbit

Pages
385–393
Paper at repository of SibFU
https://elib.sfu-kras.ru/handle/2311/19853