Attitude correction algorithm using GPS measurements for flight vehicles

For flight systems with an on-board seeker the attitude error is the major factor to determine the seeker pointing error at the time of object acquisition. To achieve a desired mission it must be minimized. The proposed algorithm corrects the attitude error in the guidance computer during flight by taking its position and velocity measurements from GPS or radar. This is possible since navigator´s position and velocity states are correlated with attitude state. Computer simulation is shown to prove the proposed algorithm.