A hybrid navigation system, composed of an Inertial Navigation System (INS) and the Global Positioning System (GPS), has been developed. The paper outlines the hybrid navigation system. The system's architecture is characterized by a correction of INS, based on GPS data and Kalman filtering techniques, so as to prevent an increase in the INS position error. To demonstrate the feasibility and the performance of the system, an engineering evaluation model was made and flight-tested in a company-owned MU-300 business jet aircraft. Test results indicate that the INS position data that are corrected by GPS data and Kalman filter closely coincide with GPS position data.
Hybrid Navigation System
1987
5 pages
Report
No indication
English
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