Systems and methods for determining location information using dual filters

System and methods of increasing reliability of determined location information by using two integration filters are provided. An exemplary embodiment integrates inertial navigation system information and global navigation satellite system (GNSS) information in a real time Kalman filter (116); determines a real time location of the aircraft with the real time Kalman filter (116) based upon the INS information and the GNSS information; delays the GNSS information by an interval; integrates the INS information and the delayed GNSS information in a delay Kalman filter (118); determines a predictive location of the aircraft with the delay Kalman filter (118) based upon the INS information, the delayed GNSS information, and the interval; and in response to an inaccuracy of the real time location determined from the real time Kalman filter (116), selects the predictive location determined from the delay Kalman filter (118) as a new real time location of the aircraft.