Gps/ins Integrated Navigation Using a Gps Antenna Array

Abstract

An integrated Global Positioning System/Inertial Navigation System (GPS/INS) navigation model is developed specifically for aerospace applications involving high vehicle dynamics. To aid attitude determination a non-dedicated multiple GPS antenna configuration is employed. Simulated results show that the resulting Extended Kalman Filter (EKF) implementation provides robust estimates of the vehicle states. Additional investigation focusses upon filter performance sensitivity to antenna noise correlation and antenna displacements.