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CubeSat Attitude Estimation via AUKF Using Magnetometer Measurements and MRPs

  • Francesco SanfedinoEmail author
  • Marco Scardino
  • Jérémie Chaix
  • Stéphanie Lizy-Destrez

Abstract

In this article the Attitude and Control system of a CubeSat is presented. The attitude estimation design approach used is based on Adaptative Unscented Kalman Filter (AUKF) using three-axismagnetometermeasurements.A set of modified Rodrigues Parameters (MRPs) is used to evaluate the attitude. Finally in order to have an complete ADCS system two control laws are introduced (Bdot and Sliding Mode) to best simulate a real CubeSat mission. The first one allows the spacecraft the control during the detumbling phase (phase at high angular rates) and in case of reaction wheels saturation and the second one is used for the nominal control (phase at low angular rates).

Keywords

Convergence Time Angular Rate Unscented Kalman Filter Attitude Control System Sigma Point 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Springer International Publishing Switzerland 2015

Authors and Affiliations

  • Francesco Sanfedino
    • 1
    Email author
  • Marco Scardino
    • 1
  • Jérémie Chaix
    • 1
  • Stéphanie Lizy-Destrez
    • 1
  1. 1.Institut Supérieur de l’Aéronautique et de l’EspaceToulouseFrance

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