Integrated Navigation Method Based on Inertial and Geomagnetic Information Fusion

High precision inertial navigation devices are required for high accuracy of on-orbit navigation of the aircraft, on the other side, it will lead to the increasement of the cost. The paper presents an integrated navigation method based on inertial and geomagnetic information fusion. This method constructs the state and the measurement equation of inertial combination and MEMS triaxial magnetometer, also uses Kalman filter algorithm based on feedback calibration. The navigation accuracy deviations are analyzed by inertial navigation in high, medium and low precision, together with the MEMS triaxial magnetometer under different accuracy of measurement. The result shows that inertial and geomagnetic information fusion navigation will decrease the accuracy requirements for inertial devices, leading to reducing the cost of the aircraft in the economic and quality and the need for installation space.