Estimation of pico-satellite attitude dynamics and external torques via Unscented Kalman Filter

Halil Ersin Söken, Chingiz Hajiyev*

*Corresponding author for this work

Research output: Contribution to journalArticlepeer-review

12 Citations (Scopus)

Abstract

In this study, an Unscented Kalman Filter (UKF) algorithm is designed for estimating the attitude of a picosatellite and the in-orbit external disturbance torques. The estimation vector is formed by the satellite's attitude, angular rates, and the unknown constant components of the external disturbance torques acting on the satellite. The gravity gradient torque, residual magnetic moment, sun radiation pressure and aerodynamic drag are all included in the estimated external disturbance torque vector. The satellite has magnetometers and gyros onboard as the attitude sensors. Because of the inherent nonlinear dynamics and the nonlinear measurement model, the UKF, which is a nonlinear version of the Kalman Filter, is selected as the filter algorithm. Performance of the proposed algorithm is demonstrated via simulations for a cube pico-satellite and the results are analyzed for different scenarios.

Original languageEnglish
Pages (from-to)149-157
Number of pages9
JournalJournal of Aerospace Technology and Management
Volume6
Issue number2
DOIs
Publication statusPublished - 2014

Keywords

  • Attitude estimation
  • Disturbance torques
  • Pico-satellite
  • Unscented Kalman filter

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