AIRCRAFT NAVIGATION METHOD Russian patent published in 2019 - IPC G01C21/12 

FIELD: aviation.

SUBSTANCE: invention relates to controlled aircrafts of various types of location. Solving said technical problem is achieved by the fact that during flight navigation of an aircraft, which includes surveying the area with onboard correlation-extremal final guidance systems (CEFGS) with reference to axes of onboard inertial navigation system (INS), comparison of the reference image, which is observed and prepared beforehand and placed in the on-board computer (BC), determination of the aircraft position by BC relative to the target and bearing on the target, – on the aircraft, placing with reference to the associated coordinate system (CS) of at least one television camera (TVC) with a photodetector array (PDA), a directory of the star field with coordinates of stars of not more than +5^m by gloss level pre-enter in BC, sidereal start-up time of aircraft, starting geographical coordinates of aircraft, after aircraft launching at its exit to passive section of trajectory (PST) by means of on-board controls, bringing angular velocities of aircraft on all axes to close to zero values from measurements of onboard INS, on PST over 20 km, at least one observation of the stellar field is carried out by means of TVC, at that, stabilization of the field of vision of the TVC as measured by the onboard INS measurements, departure of the angular position of each of the INS axes at the time of observation is determined in the BC as the difference in the values of the angular position of the direction of the stellar field reference fixed by PDA of TVC in the associated CS of the aircraft and the design direction on the same reference point relative to the axis of the INS in the associated aircraft CS, calculated values of departures of each axis of INS are stored in BC, by distance to target in BC there calculated is correction to angular position of local vertical, which is caused by curvature of earth surface, and in process of aircraft navigation performing survey of CEFGS area with reference to axes of INS with allowance for calculated departures and corrections.

EFFECT: design of a method of navigating an aircraft with radar and / or optical CEFGS, which makes it possible to rationally from the position of the criterion "efficiency-cost" realize the required accuracy of binding of the observed images of the terrain when using the on-board INS with a level of accuracy not higher than the average.

13 cl, 2 dwg