Correction Method for Aircraft Navigation System

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.