Improving the attitude determination accuracy for nanosatellites using MEMS sensors

Abstract

In this thesis, the method of increasing attitude determination accuracy was studied. Angular velocity from the camera was used for configuration of EKF. Since EKF is the error state Kalman filter, the sensitivity matrix was calculated by taking partial derivatives of the error state to the nominal observation matrix. The sensor model and space environment were investigated in detail. Finally, the verification showed that the attitude determination and control accuracy with the low cost and performance sensors were well satisfied within the requirements of the Earth observation missions.