Integrated Navigation System Based on Low Precision Fiber Optic Gyroscope

Aiming at the practical engineering requirement, design the flight test method for integrated navigation system based on low precision fiber optic gyroscope. Establish integrated navigation system based on low precision fiber optic gyroscope, including magnetic sensor, Doppler radar, and satellite navigation subsystem, design Kalman filter. Put forward the status equation and measurement equation, and carry out flight test. The test results show that the integrated navigation system can satisfy medium precision navigation requirements, with low design cost, and the system algorithm is scientific and feasible. The system is practical and can be widely used in civil aviation navigation field.