Introduction
The advent of GNSS, Global Navigation Satellite Systems has brought about an additional navigational aid for aircrafts. The use of GNSS (specifically, Global Positioning System) receivers has become commonplace in the aircrafts of today. Due to their complementary error characteristic, approaches involving GPS coupled with the INS (Inertial Navigation System) are being looked into for complete navigation and attitude estimation of the aircraft.
Overview of Project
In order to understand and develop the application of GPS in aircrafts, a simplified model concerning GPS in aircrafts (assuming decoupled and perfect INS), which included design of an Extended Kalman Filter for GPS, was studied and simulated. This report presents the development of the model, assumptions involved, and simulation results for the same. The work presented in this report will be used toward the II Stage of the B.Tech Project which will focus on GNSS- INS integration.