A Study on Real-Time Inertia Estimation Method for STSAT-3

과학기술위성 3호 실시간 관성모멘트 추정 기법 연구

  • 김광진 (현대자동차 연구소) ;
  • 이상철 (한국항공대학교 항공우주 및 기계공학부) ;
  • 오화석 (한국항공대학교 항공우주 및 기계공학부)
  • Received : 2012.11.16
  • Accepted : 2012.12.19
  • Published : 2012.12.31


The accurate information of mass properties is required for the precise control of the spacecraft. The mass properties, mass and inertia, are changeable by some reasons such as consumption of propellant, deployment of solar panel, sloshing, environmental effect, etc. The gyro-based attitude data including noise and bias reduces the control accuracy so it needs to be compensated for improvement. This paper introduces a real-time inertia estimation method for the attitude determination of STSAT-3, Korea Science Technology Satellite. In this method we first filter the gyro noise with the Extended Kalman Filter(EKF), and then estimate the moment of inertia by using the filtered data from the EKF based on the Recursive Least Square(RLS).



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