INS/GPS Integrated Navigation Technology for Hypersonic UAV

INS/GPS integrated navigation system is studied in this paper for the hypersonic UAV in order to satisfy the precise guidance requirements of hypersonic UAV and in response to the defects while the inertial navigation system (INS) and the global positioning system (GPS) are being applied separately. The information of UAV including position, velocity and attitude can be obtained by using INS and GPS respectively after generating a reference trajectory. The corresponding errors of two navigation systems can be obtained through comparing the navigation information of the above two guidance systems. Kalman filter is designed to estimate the navigation errors and then the navigation information of INS are corrected. The non-equivalence relationship between the platform misalignment angle and attitude error angle are considered so that the navigation accuracy is further improved. The Simulink simulation results show that INS/GPS integrated navigation system can help to achieve higher accuracy and better antiinterference ability than INS navigation system and this system can also satisfy the navigation accuracy requirements of hypersonic UAV.