FIELD: instrument engineering.
SUBSTANCE: invention relates to the field of navigational instrument-making and can be used in systems for improving aircraft (AC) flight and landing safety. As a means of detecting interference, an onboard AC computer of an inertial navigation system (INS) is used on the board, performing prognostic calculation of coordinates of the AC location for a specific current time and converting said coordinates into corresponding design pseudo-ranges for specific navigation satellites (NS) of the working navigation constellation visible at the given moment in time by the receiving indicator of the given AC, for the same moment of time for the same NS from their real radio signals on the receiving indicator of the given AC, real codes of pseudo-range of SRNS are obtained, then design inertial and real pseudo-range codes for the corresponding NS are compared on calculator for given current time moment, wherein inadmissible difference of compared pseudo-range codes for a specific detected NS with the confirmed condition of the currently used working constellation NS suspects detected NS in radiation of interference, and if the detected difference of pseudo-range is repeated at the next moment of time, said NS indicates detection of external imitation interference from "false satellite", which is excluded from formation of coordinates of the given AC, similarly for the next moments of time, the inertial and real pseudo-ranges are compared for the corresponding constellation NS visible at this moment in time.
EFFECT: broader functional capabilities based on detecting external interference by the AC itself.
1 cl, 1 dwg
