Error analysis and on-board calibration of magnetometer in space environment exploration satellite

A magnetometer used in the sun-earth space exploration satellite is usually assembled at the tip of the boom by the action of space disturbance torque and maneuver, the installation matrix magnetometer of varies dramatically, which may lead to the low attitude determination accuracy. Based on the analysis of the magnetometer attitude determination errors, a 19 state high-fidelity measurement model of magnetometer is proposed. Combined with satellite attitude dynamics and kinematics, a 19 state Extended Kalman Filter is adopted to estimate installation matrix on-board and compensate magnetometer measurement. Then the innovative magnetometer measurement model is used to estimate satellite attitude. Finally the algorithm is validated by using the turntable experiment. Results of turntable experiment show that this method can estimate installation matrix errors under the computational requirement of On-board Computer and dramatically improve the accuracy of attitude determination and magnetometer error estimation.