Abstract
In order to meet the requirement of high reliability and fault tolerance of the aircraft, air data assisted INS/GPS fault-tolerant integrated navigation system design is proposed, to achieve optimal estimation of navigation position error, speed error and attitude error of the aircraft. The design is for the problems that inertial and integrated GPS navigation systems has poor adaptability and is vulnerable to interference in some cases. Taking advantage of internal relations and redundancy of INS, GPS and ADS information, airspeed information is combined with INS/GPS unit by Kalman filter. Simulation results show that the data fusion and filtering algorithm maintains good continuity, system accuracy and fault tolerance in the case of intermittent GPS output.
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