Spacecraft Attitude Determination Algorithm Using Magnetometer

자장계를 이용한 인공위성의 자세결정 알고리즘

  • 민현주 (인하대학교 항공우주공학과) ;
  • 김인중 (인하대학교 항공우주공학과) ;
  • 김진호 (인하대학교 항공우주공학과) ;
  • 박춘배 (인하대학교 항공우주공학과) ;
  • 용기력 (한국항공우주연구소) ;
  • 이승우 (한국항공우주연구소)
  • Published : 2000.10.01


We present 3-axis stabilized spacecraft attitude determination algorithm using the magnetometer. The magnetometer has been used as a reliable, light-weight and inexpensive sensor in attitude determination and reaction wheel momentum dumping system. Recent studies have attempted to use the magnetometer when other attitude sensor, such as star tracker, fails. The differences between the measured and computed the Earth's magnetic field components are spacecraft attitude errors. In this paper, we propose extended Kalman filter(EKF) to determine spacecraft attitude with the magnetometer data and gyro-measured body rates. We develop and simulate this algorithm using MATLAB/SIMULINK. This algorithm can be used as a backup attitude determination system.