It is retuned that automatic control with high-rate of flight of shunt aero ballistic vehicle needs receipt of navigation information real-time with necessary exactness and time of update. grounded, that by the main lack of complex navigational which are built, as a rule, on the basis of filter of Kalman, there is a large residual error of calibration of parameters of integral navigational and plenty of cycles of receipt of satellite navigation information. the method of correction of matrix of orientation in the inertial satellite navigational of aero ballistic vehicles is offered, which is based on the method of invariant control and correction and method of vector concordance, allows to provide the high-fidelity navigation of with high-rate shunt vehicle at the limited time of treatment of information. Results over of mathematical design of the offered method are brought.
aero ballistic vehicle, navigation information, navigational