The correction method of the aircraftastro-inertial system

Abstract

The accuracy increasing problem of the unmanned aerial vehicle navigation complex in an algorithmic way is investigated. The algorithmic correction schemes of navigation systems for modern high-precision unmanned aerial vehicles are considered. The error compensating method of the inertial navigation system corrected by astro-system signals is proposed. Correction is carried out in the structure of the inertial navigation system using a non-linear Kalman filter and a control algorithm. A nonlinear control algorithm based on the SDC representation method is used. Keywords unmanned aerial vehicle; inertial navigation system; astro-system; navigation complex; nonlinear Kalman filter; error model; regulator; SDC method