METHOD FOR OPTIMAL ESTIMATION OF ERRORS OF AN INERTIAL NAVIGATION SYSTEM AND ITS CORRECTION ON A FIXED GROUND LANDMARK WITH KNOWN GEOGRAPHICAL COORDINATES Russian patent published in 2020 - IPC G01C23/00 

FIELD: navigation systems.

SUBSTANCE: invention relates to measurement information systems and combat aircraft and helicopter systems, in which method is developed for optimal estimation of complete list of inertial navigation system (INS) state parameters and effective correction of navigation and flight information measured by it. Method for optimal estimation of errors of inertial navigation system and its correction along fixed landmark with known geographical coordinates includes angular tracking of fixed landmark of correction (LC) and discrete measurement of the inclined distance to it in sparing mode for the laser range finder from the sighting system composition mode with frequency of emitting parcels of 0.5–1.0 Hz and is based on combined processing of measured current viewing angles of lC and inclined distance to it, current angles of true and gyroscopic courses, roll and pitch of object and counted INS of geographical coordinates of its location and current baro-inertial height. At that, in the mode of continuous angular tracking of the lC, one-two-second time intervals between adjacent measurements of the range to the lC are filled with its ten-Hz design values, which are formed in accordance with modified, invariable to the underlying surface of the elevation procedure for determining the inclined range, involving use of the current baro-inertial height of the object, the cosine of the angle between the geographical vertical and the direction of the lC, and formed by lC measurements of reference altitude of altitude above sea level, wherein components of the absolute linear speed of the object are estimated in accordance with the kinematic model of its motion relative to the fixed ground-based optical system in the projections on the axis of the inertial coordinate system. At that, two parallel operating procedures of optimal estimation are implemented – primary and auxiliary, first of which provides evaluation of extended vector of INS state parameters and subsequent correction of its navigation and piloting parameters, and second – formation of adequate with SNS position and speed signals used in main procedure of optimal estimation as signals of ideal meter.

EFFECT: broader functional capabilities of the sighting and navigation system of modern aircraft.

1 cl, 7 dwg