الفهرس 
chapter 1Only 14 pages are availabe for public view
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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