The aircraft navigation system is considered as part of an inertial navigation system and a Doppler radar for velocity and leeway angle. During long-time functioning without correction from satellites and stationary navigation stations, the errors in the aircraft navigation system may reach unacceptable values and must be compensated. Errors of the navigation system are corrected using the control algorithm with inertial navigation system and self-organization algorithm with trend reservation. To generate control signals, non-linear trends of the inertial navigation system errors was represented in SDC form. The results of mathematical modeling have demonstrated the effectiveness of the proposed algorithmic solutions.
Correction Method for Aircraft Navigation System
2020-09-01
405605 byte
Conference paper
Electronic Resource
English
AIRCRAFT NAVIGATION SYSTEM AND METHOD FOR AIRCRAFT NAVIGATION
European Patent Office | 2018
|Aircraft navigation system and method for aircraft navigation
European Patent Office | 2019
|NAVIGATION SYSTEM AND LOCATION CORRECTION METHOD OF NAVIGATION SYSTEM
European Patent Office | 2018
|Integrated aircraft navigation system
IEEE | 2013
|