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Abstract Avionics navigation systems are constantly demanding for exploding system performance and minimizing system size. Tbt:y require higher accuracy, reliability, and robustness against Jammmg. This drives the system-integrators towards a generation based upon satellite navigation (GPS) and inertial navigation system (INS). This thesis presents the solution of GPS navigation equations operates m a stand-alone configuration in a general em ironment. On the other hand, the solution of INS equations operates in a stand-alone configuration in the same environment. And finally, the solution of integrated GPSIINS navigation system, which will provide improvements m navigation performance |