Modification of the nonlinear kalman filter in a correction scheme of aircraft navigation systems

An algorithm for correction of the navigation data of an aircraft that uses an inertial navigation system and the global positioning system (GPS) is considered. Estimation algorithms, namely, linear and nonlinear Kalman filters, are investigated. A method for modification of the nonlinear Kalman filter with the use of a genetic algorithm has been developed. To estimate the operability and accuracy of the modified nonlinear Kalman filter, simulation based on the data of a laboratory experiment conducted with the use of real navigation systems KIND34-059 and AIST-350 has been performed. The results of the laboratory experiments conducted with the use of real navigation systems have demonstrated high accuracy of data processing by the nonlinear Kalman filter modified by the genetic algorithm.